Solving Direct and Inverse Heat Conduction Problems

Jan Taler Piotr Duda Solving Direct and Inverse Heat Conduction Problems ~ Springer Preface This book is devoted t...

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Jan Taler Piotr Duda

Solving Direct and Inverse Heat Conduction Problems

~ Springer

Preface

This book is devoted to the concept of simple and inverse heat conduction problems. The process of solving direct problems is based on the temperature determination when initial and boundary conditions are known, while the solving of inverse problems is based on the search for boundary conditions when temperature properties are known, provided that temperature is the function of time, at the selected inner points of a body. In the first part of the book (Chaps. 1-5), we have discussed theoretical basis for thermal conduction in solids, motionless liquids and liquids that move in time. In the second part of the book, (Chapters 6-26), we have discussed at great length different engineering problems, which we have presented together with the proposed solutions in the form of theoretical and mathematical examples. It was our intention to acquaint the reader in a step-by-step fashion with all the mathematical derivations and solutions to some of the more significant transient and steady-state heat conduction problems with respect to both, the movable and immovable heat sources and the phenomena of melting and freezing. Lots of attention was paid to non-linear problems. The methods for solving heat conduction problems, i.e. the exact and approximate analytical methods and numerical methods, such as the finite difference method, the finite volume method, the finite element method and the boundary element method are discussed in great detail. Aside from algorithms, applicable computational programs, written in a FORTRAN language, were given. The accuracy of the results obtained by means of various numerical methods was evaluated by way of comparison with accurate analytical solutions. The presented solutions not only allow to illustrate mathematical methods used in thermal conduction but also show the methods one can use to solve concrete practical problems, for example during the designing and life-time calculations of industrial machinery, combustion engines and in refrigerating and air conditioning engineering. Many examples refer to the topic of heating and thermo-renovation of apartment buildings. The methods for solving problems involved with welding and laser technology are also discussed in great detail. This book is addressed to undergraduate and PhD students of mechanical, power, process and environmental engineering. Due to the complexity of the heat conduction problems elaborated in this book, this edition can

vi

Preface

also serve as a reference book that can be used by nuclear, industrial and civil engineers. Jan Taler is the author of the theoretical part of this book, mathematical exercises (excluding 12.1 & 12.3), and C, D & H attachments (found at the back of this book). Piotr Duda wrote in the FORTRAN language all presented programs and solved with their help exercises 7.3, 11.2-11.7, 15.1, 15.2, 15.4, 15.5, 15.7, 15.8, 15.11, 15.13, 15.15, 16.5, 16.9, 16.10, 17.7, 18.5-18.8,21.5, 21.7-21.10, 22.7, 23.3-23.7, 24.4 and 24.5. He also carried out calculations using the following programs: ANSYS (in Exercises 11.18-11.22, 12.4, 21.9 and 25.10), BETIS (in Exercise 12.4) and MathCAD (in Exercises 14.10, 16.2,16.4,17.6 and 25.10). Furthermore, Piotr Duda is the author of Exercises 12.1 and 12.3, and attachments A, B, E, F and G.

Krakow June, 2005.

Jan Taler Piotr Duda

Contents

Part I Heat Conduction Fundamentals

1

1 Fourier Law .........................................................................................•... 3 Literature

6

2 Mass and Energy Balance Equations

7

2.1 Mass Balance Equation for a Solid that Moves at an Assigned Velocity 2.2 Inner Energy Balance Equation 2.2.1 Energy Balance Equations in Three Basic Coordinate Systems 2.3 Hyperbolic Heat Conduction Equation 2.4 Initial and Boundary Conditions 2.4.1 First Kind Boundary Conditions (Dirichlet Conditions) 2.4.2 Second Kind Boundary Conditions (von Neumann Conditions) 2.4.3 Third Kind Boundary Conditions 2.4.4 Fourth Kind Boundary Conditions 2.4.5 Non-Linear Boundary Conditions 2.4.6 Boundary Conditions on the Phase Boundaries Literature u

••••••••••••••••••••••••••••••••••••••••••••••••••

3 The Reduction of Transient Heat Conduction Equations and Boundary Conditions 3.1 Linearization of a Heat Conduction Equation 3.2 Spatial Averaging of Temperature 3.2.1 A Body Model with a Lumped Thermal Capacity 3.2.2 Heat Conduction Equation for a Simple Fin with Uniform Thickness 3.2.3 Heat Conduction Equation for a Round Fin with Uniform Thickness 3.2.4 Heat Conduction Equation for a Circular Rod or a Pipe that Moves at Constant Velocity Literature

7 9

12 16 17 18 18 19 21 22 24 26

29 29 31 31 33 35 37 39

viii

Contents

4 Substituting Heat Conduction Equation by Two-Equations System 4.1 Steady-State Heat Conduction in a Circular Fin with Variable Thermal Conductivity and Transfer Coefficient 4.2 One-Dimensional Inverse Transient Heat Conduction Problem Literature

5 Variable Change Literature

41 41 43 46

47 50

Part II Exercises. Solving Heat Conduction Problems

51

6 Heat Transfer Fundamentals

53

Exercise 6.1 Fourier Law in a Cylindrical Coordinate System 53 Exercise 6.2 The Equivalent Heat Transfer Coefficient Accounting for Heat Exchange by Convection and Radiation 55 Exercise 6.3 Heat Transfer Through a Flat Single-Layered and Double-Layered Wall 57 Exercise 6.4 Overall Heat Transfer Coefficient and Heat Loss Through a Pipeline Wall 60 Exercise 6.5 Critical Thickness of an Insulation on an Outer Surface of a Pipe 62 Exercise 6.6 Radiant Tube Temperature 65 Exercise 6.7 Quasi-Steady-State of Temperature Distribution and Stresses in a Pipeline Wall 68 Exercise 6.8 Temperature Distribution in a Flat Wall with Constant and Temperature Dependent Thermal Conductivity ..... 70 Exercise 6.9 Determining Heat Flux on the Basis of Measured Temperature at Two Points Using a Flat and Cylindrical Sensor 74 Exercise 6.10 Determining Heat Flux By Means of Gardon Sensor with a Temperature Dependent Thermal Conductivity 77 Exercise 6.11 One-Dimensional Steady-State Plate Temperature Distribution Produced by Uniformly Distributed Volumetric Heat Sources 80 Exercise 6.12 One-Dimensional Steady-State Pipe Temperature Distribution Produced by Uniformly Distributed Volumetric Heat Sources 82 Exercise 6.13 Inverse Steady-State Heat Conduction Problem in a Pipe 85 Exercise 6.14 General Equation of Heat Conduction in Fins 87 Exercise 6.15 Temperature Distribution and Efficiency of a Straight Fin with Constant Thickness 89

Contents

Exercise 6.16 Temperature Measurement Error Caused by Thermal Conduction Through Steel Casing that Contains a Thermoelement as a Measuring Device Exercise 6.17 Temperature Distribution and Efficiency of a Circular Fin of Constant Thickness Exercise 6.18 Approximated Calculation of a Circular Fin Efficiency Exercise 6.19 Calculating Efficiency of Square and Hexagonal Fins Exercise 6.20 Calculating Efficiency of Hexagonal Fins by Means of an Equivalent Circular Fin Method and Sector Method Exercise 6.21 Calculating Rectangular Fin Efficiency Exercise 6.22 Heat Transfer Coefficient in Exchangers with Extended Surfaces Exercise 6.23 Calculating Overall Heat Transfer Coefficient in a Fin Plate Exchanger Exercise 6.24 Overall Heat Transfer Coefficient for a Longitudinally Finned Pipe with a Scale Layer on an Inner Surface Exercise 6.25 Overall Heat Transfer Coefficient for a Longitudinally Finned Pipe Exercise 6.26 Determining One-Dimensional Temperature Distribution in a Flat Wall by Means of Finite Volume Method Exercise 6.27 Determining One-Dimensional Temperature Distribution in a Cylindrical Wall by Means of Finite Volume Method Exercise 6.28 Inverse Steady-State Heat Conduction Problem for a Pipe Solved by Space-Marching Method Exercise 6.29 Temperature Distribution and Efficiency of a Circular Fin with Temperature-Dependent Thermal Conductivity Literature

7 Two-Dimensional Steady-State Heat Conduction. Analytical Solutions Exercise 7.1 Temperature Distribution in an Infinitely Long Fin with Constant Thickness Exercise 7.2 Temperature Distribution in a Straight Fin with Constant Thickness and Insulated Tip Exercise 7.3 Calculating Temperature Distribution and Heat Flux in a Straight Fin with Constant Thickness and Insulated Tip

ix

92 95 98 99

102 108 109 114

115 119 122

127 131

134 138

141 141 145 148

x

Contents

Exercise 7.4 Temperature Distribution in a Radiant Tube of a Boiler Literature

8 Analytical Approximation Methods. Integral Heat Balance Method Exercise 8.1 Temperature Distribution within a Rectangular CrossSection of a Bar Exercise 8.2 Temperature Distribution in an Infinitely Long Fin of Constant Thickness Exercise 8.3 Determining Temperature Distribution in a Boiler's Water-Wall Tube by Means of Functional Correction Method Literature

9 Two-Dimensional Steady-State Heat Conduction. Graphical Method

156 160

161 161 163

165 169

171

Exercise 9.1 Temperature Gradient and Surface-Transmitted Heat Flow 171 Exercise 9.2 Orthogonality of Constant Temperature Line and Constant Heat Flux 173 Exercise 9.3 Determining Heat Flow between Isothermal Surfaces .. 176 Exercise 9.4 Determining Heat Loss Through a Chimney Wall; Combustion Channel (Chimney) with Square Cross-Section 179 Exercise 9.5 Determining Heat Loss Through Chimney Wall with a Circular Cross-Section 181 Literature 182

10 Two-Dimensional Steady-State Problems. The Shape Coefficient Exercise 10.1 Buried Pipe-to-Ground Surface Heat Flow Exercise 10.2 Floor Heating Exercise 10.3 Temperature of a Radioactive Waste Container Buried Underground Literature

11 Solving Steady-State Heat Conduction Problems by Means of Numerical Methods Exercise 11.1 Description of the Control Volume Method Exercise 11.2 Determining Temperature Distribution in a Square Cross-Section of a Long Rod by Means of the Finite Volume Method

183 183 185 186 187

189 189

194

Contents

Exercise 11.3 A Two-Dimensional Inverse Steady-State Heat Conduction Problem Exercise 11.4 Gauss-Seidel Method and Over-Relaxation Method Exercise 11.5 Determining Two-Dimensional Temperature Distribution in a Straight Fin with Uniform Thickness by Means of the Finite Volume Method Exercise 11.6 Determining Two-Dimensional Temperature Distribution in a Square Cross-Section of a Chimney Exercise 11.7 Pseudo-Transient Determination of Steady-State Temperature Distribution in a Square Cross-Section of a Chimney; Heat Transfer by Convection and Radiation on an Outer Surface of a Chimney Exercise 11.8 Finite Element Method Exercise 11.9 Linear Functions That Interpolate Temperature Distribution (Shape Functions) Inside Triangular and Rectangular Elements Exercise 11.10 Description of FEM Based on Galerkin Method Exercise 11.11 Determining Conductivity Matrix for a Rectangular and Triangular Element Exercise 11.12 Determining Matrix [:K/] in Terms of Convective Boundary Conditions for a Rectangular and Triangular Element e Exercise 11.13 Determining Vector {fQ } with Respect to Volumetric and Point Heat Sources in a Rectangular and Triangular Element e e Exercise 11.14 Determining Vectors {fq } and {fa } with Respect to Boundary Conditions of 2nd and 3rd Kind on the Boundary of a Rectangular or Triangular Element Exercise 11.15 Methods for Building Global Equation System in FEM Exercise 11.16 Determining Temperature Distribution in a Square Cross-Section of an Infinitely Long Rod by Means of FEM, in which the Global Equation System is Constructed using Method I (from Ex. 11.15) Exercise 11.17 Determining Temperature Distribution in an Infinitely Long Rod with Square Cross-Section by Means of FEM, in which the Global Equation System is Constructed using Method II (from Ex. 11.15) Exercise 11.18 Determining Temperature Distribution by Means of FEM in an Infinitely Long Rod with Square Cross-Section, in which Volumetric Heat Sources Operate Exercise 11.19 Determining Two-Dimensional Temperature Distribution in a Straight Fin with Constant Thickness by Means of FEM

xi

199 204

208 215

221 230

234 238 245 249

253

256 259

264

271

275

285

xii

Contents

Exercise 11.20 Determining Two-Dimensional Temperature Distribution by Means of FEM in a Straight Fin with Constant Thickness (ANSYS Program) 297 Exercise 11.21 Determining Two-Dimensional Temperature Distribution by Means of FEM in a Hexagonal Fin with Constant Thickness (ANSYS Program) 300 Exercise 11.22 Determining Axisymmetrical Temperature Distribution in a Cylindrical and Conical Pin by Means of FEM (ANSYS program) 303 Literature 307

12 Finite Element Balance Method and Boundary Element Method Exercise 12.1 Finite Element Balance Method Exercise 12.2 Boundary Element Method Exercise 12.3 Determining Temperature Distribution in Square Region by Means of FEM Balance Method Exercise 12.4 Determining Temperature Distribution in a Square Region Using Boundary Element Method Literature

309 309 314 323 327 331

13 Transient Heat Exchange Between a Body with Lumped Thermal Capacity and Its Surroundings 333 Exercise 13.1 Heat Exchange between a Body with Lumped Thermal Capacity and Its Surroundings 333 Exercise 13.2 Heat Exchange between a Body with Lumped Thermal Capacity and Surroundings with Time-Dependent Temperature 336 Exercise 13.3 Determining Temperature Distribution of a Body with Lumped Thermal Capacity, when the Temperature of a Medium Changes Periodically 339 Exercise 13.4 Inverse Problem: Determining Temperature of a Medium on the Basis of Temporal Thermometer-Indicated Temperature History 340 Exercise 13.5 Calculating Dynamic Temperature Measurement Error by Means of a Thermocouple 342 Exercise 13.6 Determining the Time It Takes to Cool Body Down to a Given Temperature 344 Exercise 13.7 Temperature Measurement Error of a Medium whose Temperature Changes at Constant Rate 345 Exercise 13.8 Temperature Measurement Error of a Medium whose Temperature Changes Periodically 346

Contents

Exercise 13.9 Inverse Problem: Calculating Temperature of a Medium whose Temperature Changes Periodically, on the Basis of Temporal Temperature History Indicated by a Thermometer Exercise 13.10 Measuring Heat Flux Literature

14 Transient Heat Conduction in Half-Space

xiii

347 349 351

353

Exercise 14.1 Laplace Transform 353 Exercise 14.2 Formula Derivation for Temperature Distribution in a Half-Space with a Step Increase in Surface Temperature 355 Exercise 14.3 Formula Derivation for Temperature Distribution in a Half-Space with a Step Increase in Heat Flux 358 Exercise 14.4 Formula Derivation for Temperature Distribution in a Half-Space with a Step Increase in Temperature of a Medium 360 Exercise 14.5 Formula Derivation for Temperature Distribution in a Half-Space when Surface Temperature is Time-Dependent. 364 Exercise 14.6 Formula Derivation for a Quasi-Steady State Temperature Field in a Half-Space when Surface Temperature Changes Periodically 366 Exercise 14.7 Formula Derivation for Temperature of Two Contacting Semi-Infinite Bodies 374 Exercise 14.8 Depth of Heat Penetration 375 Exercise 14.9 Calculating Plate Surface Temperature under the Assumption that the Plate is a Semi-Infinite Body 377 Exercise 14.10 Calculating Ground Temperature at a Specific Depth 378 Exercise 14.11 Calculating the Depth of Heat Penetration in the Wall of a Combustion Engine 379 Exercise 14.12 Calculating Quasi-Steady-State Ground Temperature at a Specific Depth when Surface Temperature Changes Periodically 380 Exercise 14.13 Calculating Surface Temperature at the Contact Point of Two Objects 382 Literature 383

15 Transient Heat Conduction in Simple-Shape Elements

385

Exercise 15.1 Formula Derivation for Temperature Distribution in a Plate with Boundary Conditions of 3rd Kind 385 Exercise 15.2 A Program for Calculating Temperature Distribution and Its Change Rate in a Plate with Boundary Conditions of 3rd Kind 394

XIV

Contents

Exercise 15.3 Calculating Plate Surface Temperature and Average Temperature Across the Plate Thickness by Means of the Provided Graphs 398 Exercise 15.4 Formula Derivation for Temperature Distribution in an Infinitely Long Cylinder with Boundary Conditions of 3rd Kind 402 Exercise 15.5 A Program for Calculating Temperature Distribution and Its Change Rate in an Infinitely Long Cylinder with Boundary Conditions of 3rd Kind 412 Exercise 15.6 Calculating Temperature in an Infinitely Long Cylinder using the Annexed Diagrams 416 Exercise 15.7 Formula Derivation for a Temperature Distribution in a Sphere with Boundary Conditions of 3rd Kind 420 Exercise 15.8 A Program for Calculating Temperature Distribution and Its Change Rate in a Sphere with Boundary Conditions of 3rd Kind 428 Exercise 15.9 Calculating Temperature of a Sphere using the Diagrams Provided 432 Exercise 15.10 Formula Derivation for Temperature Distribution in a Plate with Boundary Conditions of 2nd Kind 436 Exercise 15.11 A Program and Calculation Results for Temperature Distribution in a Plate with Boundary Conditions of 2nd Kind 441 Exercise 15.12 Formula Derivation for Temperature Distribution in an Infinitely Long Cylinder with Boundary Conditions of 2nd Kind 444 Exercise 15.13 Program and Calculation Results for Temperature Distribution in an Infinitely Long Cylinder with Boundary Conditions of 2nd Kind 448 Exercise 15.14 Formula Derivation for Temperature Distribution in a Sphere with Boundary Conditions of 2nd Kind 452 Exercise 15.15 Program and Calculation Results for Temperature Distribution in a Sphere with Boundary Conditions of 2nd kind 456 Exercise 15.16 Heating Rate Calculations for a Thick-Walled Plate 460 Exercise 15.17 Calculating the Heating Rate of a Steel Shaft 461 Exercise 15.18 Determining Transients of Thermal Stresses in a Cylinder and a Sphere 463 Exercise 15.19 Calculating Temperature and Temperature Change Rate in a Sphere 464

Contents Exercise 15.20 Calculating Sensor Thickness for Heat Flux Measuring Literature

16 Superposition Method in One-Dimensional Transient Heat Conduction Problems

xv

465 467

469

Exercise 16.1 Derivation of Duhamel Integral 469 Exercise 16.2 Derivation of an Analytical Formula for a Half-Space Surface Temperature when Medium's Temperature 472 Undergoes a Linear Change in the Function of Time Exercise 16.3 Derivation of an Approximate Formula for a Half-Space Surface Temperature with an Arbitrary Change 476 in Medium's Temperature in the Function of Time Exercise 16.4 Derivation of an Approximate Formula for a Half-Space Surface Temperature when Temperature of a Medium Undergoes a Linear Change in the Function of Time ... 479 Exercise 16.5 Application of the Superposition Method when Initial Body Temperature is Non-Uniform 481 Exercise 16.6 Description of the Superposition Method Applied to Heat Transfer Problems with Time-Dependent 484 Boundary Conditions Exercise 16.7 Formula Derivation for a Half-Space Surface Temperature with a Change in Surface Heat Flux 488 in the Form of a Triangular Pulse Exercise 16.8 Formula Derivation for a Half-Space Surface Temperature with a Mixed Step-Variable Boundary Condition in Time 491 Exercise 16.9 Formula Derivation for a Plate Surface Temperature with a Surface Heat Flux Change in the Form of a Triangular Pulse and the Calculation of this Temperature 495 Exercise 16.10 Formula Derivation for a Plate Surface Temperature with a Surface Heat Flux Change in the Form of a Rectangular Pulse; Temperature Calculation 500 Exercise 16.11 A Program and Calculation Results for a Half-Space Surface Temperature with a Change 503 in Surface Heat Flux in the Form of a Triangular Pulse Exercise 16.12 Calculation of a Half-Space Temperature with a Mixed Step-Variable Boundary Condition in Time 506 Exercise 16.13 Calculating Plate Temperature by Means of the Superposition Method with Diagrams Provided 507 Exercise 16.14 Calculating the Temperature of a Paper in an Electrostatic Photocopier 509 Literature 513

xvi

Contents

17 Transient Heat Conduction in a Semi-Infinite body. The Inverse Problem 515 Exercise 17.1 Measuring Heat Transfer Coefficient. The Transient Method 515 Exercise 17.2 Deriving a Formula for Heat Flux on the Basis of Measured Half-Space Surface Temperature Transient Interpolated by a Piecewise Linear Function 518 Exercise 17.3 Deriving Heat Flux Formula on the Basis of a Measured and Polynomial-Approximated Half-Space Surface Temperature Transient 521 Exercise 17.4 Formula Derivation for a Heat Flux Periodically Changing in Time on the Basis of a Measured Temperature Transient at a Point Located under the Semi-Space Surface 523 Exercise 17.5 Deriving a Heat Flux Formula on the Basis of Measured Half-Space Surface Temperature Transient, Approximated by a Linear and Square Function 527 Exercise 17.6 Determining Heat Transfer Coefficient on the Plexiglass Plate Surface using the Transient Method 528 Graphical Method.~ 529 Numerical Method 529 Exercise 17.7 Determining Heat Flux on the Basis of a Measured Time Transient of the Half-Space Temperature, Approximated by a Piecewise Linear Function 532 Exercise 17.8 Determining Heat Flux on the Basis of Measured Time Transient of a Polynomial-Approximated Half-Space Temperature 535 Literature 539

541 18 Inverse Transient Heat Conduction Problems Exercise 18.1 Derivation of Formulas for Temperature Distribution and Heat Flux in a Simple-Shape Bodies on the Basis of a Measured Temperature Transient in a Single Point 541 Plate 543 Cylinder 543 Sphere 544 Exercise 18.2 Formula Derivation for a Temperature of a Medium when Linear Time Change in Plate Surface Temperature is Assigned 545 Exercise 18.3 Determining Temperature Transient of a Medium for which Plate Temperature at a Point with a Given Coordinate Changes According to the Prescribed Function 547

Contents

xvii

Exercise 18.4 Formula Derivation for a Temperature of a Medium, which is Warming an Infinite Plate; Plate Temperature at a Point with a Given Coordinate Changes at Constant Rate 549 Exercise 18.5 Determining Temperature and Heat Flux on the Plate Front Face on the Basis of a Measured Temperature Transient on an Insulated Back Surface; Heat Flow on the Plate Surface is in the Form of a Triangular Pulse 555 Exercise 18.6 Determining Temperature and Heat Flux on the Surface of a Plate Front Face on the Basis of a Measured Temperature Transient on an Insulated Back Surface; Heat Flow on the Plate Surface is in the Form of a Rectangular Pulse 562 Exercise 18.7 Determining Time-Temperature Transient of a Medium, for which the Plate Temperature at a Point with a Given Coordinate Changes in a Linear Way 565 Exercise 18.8 Determining Time-Temperature Transient of a Medium, for which the Plate Temperature at a Point with a Given Coordinate Changes According to the Square Function Assigned 569 Literature 571

19 Multidimensional Problems. The Superposition Method 573 Exercise 19.1 The Application of the Superposition Method to Multidimensional Problems 573 Exercise 19.2 Formula Derivation for Temperature Distribution in a Rectangular Region with a Boundary Condition of 3rd Kind ..... 577 Exercise 19.3 Formula Derivation for Temperature Distribution in a Rectangular Region with Boundary Conditions of 2nd Kind 580 Exercise 19.4 Calculating Temperature in a Steel Cylinder of a Finite Height 582 Exercise 19.5 Calculating Steel Block Temperature 584 20 Approximate Analytical Methods for Solving Transient Heat Conduction Problems Exercise 20.1 Description of an Integral Heat Balance Method by Means of a One-Dimensional Transient Heat Conduction Example Exercise 20.2 Determining Transient Temperature Distribution in a Flat Wall with Assigned Conditions of 1st, 2nd and 3rd Kind Exercise 20.3 Determining Thermal Stresses in a Flat Wall Literature

587

587 590 600 600

xviii

Contents

21 Finite Difference Method 605 Exercise 21.1 Methods of Heat Flux Approximation on the Plate surface 606 Exercise 21.2 Explicit Finite Difference Method with Boundary Conditions of 1st, 2nd and 3rd Kind 610 Exercise 21.3 Solving Two-Dimensional Problems by Means of the Explicit Difference Method 616 Exercise 21.4 Solving Two-Dimensional Problems by Means of the Implicit Difference Method 622 Exercise 21.5 Algorithm and a Program for Solving a Tridiagonal Equation System by Thomas Method 626 Exercise 21.6 Stability Analysis of the Explicit Finite Difference Method by Means of the von Neumann Method 630 Exercise 21.7 Calculating One-Dimensional Transient Temperature Field by Means of the Explicit Method and a Computational Program 634 Exercise 21.8 Calculating One-Dimensional Transient Temperature Field by Means of the Implicit Method and a Computational Program 639 Exercise 21.9 Calculating Two-Dimensional Transient Temperature Field by Means of the Implicit Method and a Computational Program; Algebraic Equation System is Solved by Gaussian Elimination Method 644 Exercise 21.10 Calculating Two-Dimensional Transient Temperature Field by Means of the Implicit Method and a Computational Program; Algebraic Equation System Solved by Over-Relaxation Method 652 Literature 656 22 Solving Transient Heat Conduction Problems by Means of Finite Element Method (FEM) Exercise 22.1 Description of FEM Based on Galerkin Method Used for Solving Two-Dimensional Transient Heat Conduction Problems Exercise 22.2 Concentrating (Lumped) Thermal Finite Element Capacity in FEM Exercise 22.3 Methods for Integrating Ordinary Differential Equations with Respect to Time Used in FEM Exercise 22.4 Comparison of FEM Based on Galerkin Method and Heat Balance Method with Finite Volume Method Exercise 22.5 Natural Coordinate System for One-Dimensional, Two-Dimensional Triangular and Two-Dimensional Rectangular Elements

659

659 662 668 671

674

Contents Exercise 22.6 Coordinate System Transformations and Integral Calculations by Means of the Gauss-Legendre Quadratures Exercise 22.7 Calculating Temperature in a Complex-Shape Fin by Means of the ANSYS Program Literature

xix

678 687 690

23 Numerical-Analytical Methods 693 Explicit Method 694 Implicit Method 694 Crank-Nicolson Method 694 Exercise 23.1 Integration of the Ordinary Differential Equation System by Means of the Runge- Kutta Method 695 Exercise 23.2 Numerical-Analytical Method for Integrating a Linear Ordinary Differential Equation System 698 Exercise 23.3 Determining Steel Plate Temperature by Means of the Method of Lines, while the Plate is Cooled by air and Boiling Water 703 Exercise 23.4 Using the Exact Analytical Method and the Method of lines to Determine Temperature of a Cylindrical Chamber 709 Exercise 23.5 Determining Thermal Stresses in a Cylindrical Chamber using the Exact Analytical Method and the Method of Lines 714 Exercise 23.6 Determining Temperature Distribution in a cylindrical Chamber with Constant and Temperature Dependent Thermo- Physical Properties by Means of the Method of Lines 718 Exercise 23.7 Determining Transient Temperature Distribution in an Infinitely Long Rod with a Rectangular Cross-Section by Means of the Method of Lines 724 Literature 729 24 Solving Inverse Heat Conduction Problems by Means of Numerical Methods 733 Exercise 24.1 Numerical-Analytical Method for Solving Inverse Problems 733 Exercise 24.2 Step-Marching Method in Time Used for Solving Non-Linear Transient Inverse Heat Conduction Problems 739 Exercise 24.3 Weber Method Step-Marching Methods in Space 746 Exercise 24.4 Determining Temperature and Heat Flux Distribution in a Plate on the Basis of a Measured Temperature on a Thermally Insulated Back Plate Surface; Heat Flux is in the Shape of a Rectangular Pulse 751

xx

Contents

Exercise 24.5 Determining Temperature and Heat Flux Distribution in a Plate on the Basis of a Temperature Measurement on an Insulated Back Plate Surface; Heat Flux is in the Shape of a Triangular Pulse 759 Literature 763

25 Heat Sources Exercise 25.1 Determining Formula for Transient Temperature Distribution Around an Instantaneous (Impulse) Point Heat Source Active in an Infinite Space Exercise 25.2 Determining Formula for Transient Temperature Distribution in an Infinite Body Produced by an Impulse Surface Heat Source Exercise 25.3 Determining Formula for Transient Temperature Distribution Around Instantaneous Linear Impulse Heat Source Active in an Infinite Space Exercise 25.4 Determining Formula for Transient Temperature Distribution Around a Point Heat Source, which lies in an Infinite Space and is Continuously Active Exercise 25.5 Determining Formula for a Transient Temperature Distribution Triggered by a Surface Heat Source Continuously Active in an Infinite Space Exercise 25.6 Determining Formula for a Transient Temperature Distribution Around a Continuously Active Linear Heat Source with Assigned Power 'q per Unit of Length

765

767

770

772

774

777

779

Exercise 25.7 Determining Formula for Quasi-Steady-State Temperature Distribution Caused by a Point Heat Source with a Power

00 that Moves at Constant Velocity v

in Infinite Space or on the Half Space Surface Exercise 25.8 Determining Formula for Transient Temperature Distribution Produced by a Point Heat Source with Power Qo that Moves At Constant Velocity v in Infinite Space or on the Half Space Surface Exercise 25.9 Calculating Temperature Distribution along a Straight Line Traversed by a Laser Beam Exercise 25.10 Quasi-Steady State Temperature Distribution in a Plate During the Welding Process; a Comparison between the Analytical Solution and FEM Literature 00.0000.00000 ••• 0

0

0

0

0

0

0

•• 0

0

0

0

781

785 789

0.0

792 796

Contents

xxi

26 Melting and Solidification (Freezing)...•...•...•.................•........••....•. 799 Exercise 26.1 Determination of a Formula which Describes the Solidification (Freezing) and Melting of a Semi-Infinite Body (the Stefan Problem) 803 Exercise 26.2 Derivation of a Formula that Describes the Solidification (Freezing) of a Semi-Infinite Body Under the Assumption that the Temperature of a Liquid Is Non-Uniform ... 808 Exercise 26.3 Derivation of a Formula that Describes Quasi-SteadyState Solidification (Freezing) of a Flat Liquid Layer 811 Exercise 26.4 Derivation of Formulas that Describe Solidification (Freezing) of Simple-Shape Bodies: Plate, Cylinder and Sphere 816 Exercise 26.5 Ablation of a Semi-Infinite Body 820 Exercise 26.6 Solidification of a Falling Droplet of Lead 823 Exercise 26.7 Calculating the Thickness of an Ice Layer After the Assigned Time 825 Exercise 26.8 Calculating Accumulated Energy in a Melted Wax 826 Exercise 26.9 Calculating Fish Freezing Time 828 Literature 829 Appendix A Basic Mathematical Functions A.l. Gauss Error Function A.2. Hyperbolic Functions A.3. Bessel Functions Literature

831 831 833 834 835

Appendix B Thermo-Physical Properties of Solids................•............ 837 B.1. Tables of Thermo-Physical Properties of Solids 837 B.2. Diagrams 856 B.3. Approximated Dependencies for Calculating Thermo-Physical Properties of a Steel [8] 858 Literature 861 Appendix C Fin Efficiency Diagrams (for Chap. 6, Part 11) Literature

863 865

Appendix D Shape Coefficients for Isothermal Surfaces with Different Geometry (for Chap. 10, part 11)

867

Appendix E Subprogram for Solving Linear Algebraic Equations System using Gauss Elimination Method (for Chap. 6, Part 11) 879 Appendix F Subprogram for Solving a Linear Algebraic Equations System by Means of Over-Relaxation Method 881

xxii

Contents

Appendix G Subprogram for Solving an Ordinary Differential Equations System of 1st order using Runge-Kutta Method of 4th Order (for Chap. 11, Part II)

883

Appendix H Determining Inverse Laplace Transform for Chap. 15, Part II)

885

Literature

889

Nomenclature

a

a,b A

A b Bi C

< c, c* C d,D

dw dz d D e

E E

f F

Fo g [g] h h hsl

2/s

thermal diffusivity, m length of rectangle sides, m surface area, m' matrix of the algebraic equation coefficients vector of the coefficients from the right side of an equation Biot number aliA specific heat, J/(kg·K) specific heat at constant pressure, J/(kg· K) specific heat at constant volume, J/(kg· K) specific heat substitute, J/(kg· K) an inverse matrix to A coefficients matrix diameter, m inner diameter, m outer diameter, m directional versor pulse duration, s coordinates versor longitudinal elasticity modulus (Young modulus), MPa distance of a temperature sensor from a solid's surface, m measured temperature, in °C or K dimensionless measured temperature 2 Fourier number (at/L ) thickness, m column vector of temperature gradient enthalpy, J/kg height, m latent heat of melting (change in enthalpy due to a change from a solid to liquid phase), J/kg dimensionless heat flux enthalpy, J/kg current, A modified Bessel function of the first kind of order zero modified Bessel function of the first kind of order one Bessel function of the first kind of order zero Bessel function of the first kind of order one overall heat transfer coefficient, W/(m .K) dimensionless heat transfer coefficient modified Bessel function of the second kind of order zero modified Bessel function of the second kind of order one

xxiv

Nomenclature

L L

Lc L

i; L y '

t;

m m

n

».e ny' n,

Nj p

P P

r;». q q

length, m fin height, m equivalent fin height, m latent heat of melting, J/kg length in x, y, z direction, m mass, kg fin parameter (2a1At)0.5 ,11m outwardly directed unit normal vector to the control volume boundary directional cosinuses shape function for i- node of a finite element e pressure, MPa perimeter, m temperature-change duratioon, s perpendicular and linear pitch to the direction of air flow, m 2 energy per unit of surface, J/m a variable in Laplace transform q =

;;r;

energy per unit of length, Jim 2 heat flux, W/m 2 thermal load of heat furnace wall (absorbed heat flux), W/m energy generation rate per unit volume (uniform within the 3

r

s s s S Ste

t t t t tu T

r, Tcz Tm

t; r,

r,

Tp Tsp

body), W/m heat flow, W radius, m inner surface radius, m outer surface radius, m heat resistance, KJW phase boundary position, m complex variable fin spacing, m shape coefficient, m Stefan number c (Tm - To)lh sl time, s width, m fin width, m water-wall tube spacing, m time of heat flux step-change, s temperature, °C or K fin base temperature, °C or K fluid temperature, °C or K melting temperature, °C or K mean temperature over the wall thickness, °C or K temperature in z-node, °C or K external temperature during radiation heat transfer, K air temperature, °C or K temperature of combustion gases, °C or K

Nomenclature

To T T

u u u(r, t)

U U

W

W x'

wy'

x,y,z

X Y Yo Y1

Wz

xxv

initial temperature, °C or K mean temperature, °C or K Laplace transform inner energy, J/kg transformed temperature, temperature difference (T - To)' K influence function (system response to unit step function) voltage, V Laplace transform 3/kg specific volume, m velocity, m/s temperature change rate, Kls or Klmin volume, m' width, m velocity components, m/s Cartesian coordinates dimensionless coordinate smoothed temperature, °C or K Bessel function of the second kind of order zero Bessel function of the second kind of order one

Greek symbols a

f3 r

s s

~t

~T ~,~r &

e 1] 1]

g

e e

Jln v ~ p p

a

2·K)

heat transfer coefficient, W/(m linear or volumetric thermal expansion coefficient, 11K unit step function (Heaviside function) depth of heat penetration, m Dirac function time step, s temperature difference, K spatial step in the x or r direction, m surface emissivity temperature measurement error, K fin efficiency similarity variable (dimensionless coordinate) angle coordinate dimensionless temperature excess temperature (temperature difference between true and initial temperature or between true and ambient temperature), K 2/s thermal diffusivity, m thermal conductivity, W/(m·K) thermal conductivity in x, y, z direction, W/(m·K) thermal conductivity tensor n-th root of a characteristic equation Poisson ratio a coordinate in moving coordinate system, m density, kg/m' dimensionless radius Stefan-Boltzmann constant, 5.67.10- 8 W/(m 2·K4 )

xxvi

Nomenclature radial, tangential and axial stresses respectively, MPa relaxation time, s time constant, s angle coordinate 3 dissipation function, W/m circular frequency, lis

PART Heat Conduction Fundamentals Heat conduction is, aside from convection and radiation, the basic form of heat transfer. It is the only type of heat flow that occurs in non-transparent solids. In the cases of gases and fluids, heat conduction usually occurs in combination with other forms of conduction, such as convection and radiation.

1 Fourier Law

In order to describe heat conduction phenomena, one usually uses a law formulated by Fourier [2], which has the following form for onedimensional problems:

q" =-1 aT

(1.1)

ax '

where, q is the heat flux expressed in W/m , A - a thermal conductivity in W/(m·K), T - a temperature in °C or K, while x - a coordinate in m. The minus sign in (1.1) testifies to the fact that heat flows in the direction of the decreasing temperature. Therefore, derivative oT/ox is negative (Fig. 1.1), so in order to obtain positive value q, the minus sign occurs on the right side of (1.1). In such a case, the direction of x axis and of the heat flux vector are the same. 2

a)

b)

T

T

oT 0

Ox

Ox

heat conduction

heat conduction

c:::>

~ x

x

Fig. 1.1. Schematic diagram that illustrates the sign change of the first derivative of function T(x, t), which describes temperature changes

If T(x, t) is an increasing function (Fig. 1.1b), then one obtains a negative value of q from (1.1). If one assumes that the value of heat flux q is

4

1 Fourier Law

always positive, then the minus sign in (1.1) should be omitted in the case depicted in Fig. 1.1b. In general, the heat flux vector is defined by Fourier law

q =-AVT,

(1.2)

where, V T = grad T is a temperature gradient, a right angle vector to an isothermic surface turned in the direction of a given point, where the function increases most rapidly. Hamiltonian vectorial operator, also described as nabla, has the following form in the three basic coordinate systems: • in the Cartesian coordinate system (x, y, z) (Fig. 1.2a)

a ax

a ay

a' az

(1.3)

V =ex-+ey-+e z -

where, ex =i, ey =J., ez =k, • in the cylindrical coordinate system(r, 0, z) (Fig. 1.2b)

a 1a r ar ° rao

a z az '

V=e -+e --+e -

(1.4)

• in the spherical coordinate system (r, 0, cp) (Fig. 1.2c)

a

a

ar

() r aB

a

I I V=e -+e --+e - - r

({J

(1.5)

rsinO alp ,

where unit vectors e,x ey , eZ, er , eo, eZ and e,r eo, em, constitute an orthogonal -r local base in the Cartesian, cylindrical and spherical coordinate system respectively. If Hamiltonian operator is known (1.3-1.5), it is easy to write a heat conduction equation in different coordinate systems. Thermal conductivity c)

b)

a)

z

z

..........

/

x

y

r

x

x

y'

Fig. 1.2. Orthogonal coordinate systems: a) cartesian, b) cylindrical, c) spherical

1 Fourier Law

5

A may be temperature or location dependent. For isotropic bodies, the thermal conductivity is a scalar. In the case of anisotropic bodies, the heat conduction coefficient is a 2nd order symmetrical tensor. Fourier Law has in this case the following form:

q =-A·VT,

(1.6)

where A is a 2nd order symmetrical tensor

-,

-,

Axy A= Ayx Ayy

-,

Azy

Azz

-,

(1.7)

Therefore, the coordinates of the heat flux vector have in the Cartesian coordinate system the following forms:

·

(aT aT aT] ax By az · =- (aT et aT] , qy AYX-+Ayy-+Ayzax By az qx =- Axx-+Axy-+Axz - ,

(1.8)

· (aTax + A orBy + Azz &aT] ·

qz = - Azx

zy

It can be proved that it is always possible to find three mutually orthogonal directions in space, such that Aij

:;t: 0

for

i= j ,

Aij = 0

for

i :j:. j .

(1.9)

These directions are called the principal directions of an anisotropic body. When principal directions are parallel to an axis of an assumed coordinate system, the conduction tensor is simplified to the following form:

A= 0

(1.10)

o Heat flux vector components are then defined as follow:

.

A

qx =- xx

aT

ax '

(1.11)

6

1 Fourier Law

Heat flux normal component on the body's surface is defined using the following formula:

q. n = -A· V'T·n = (llxnx + «», + qznz) ,

(1.12)

where, nx=cos(n,x), ny=cos(n,y), nz=cos(n,z) are directional cosinuses of a normal to a surface. If heat flow reaches the body surface, then the product it· n has a negative value, since angle tp between normal n directed to the outside of the body and heat flow it directed to the inside of the body is larger than Te12. Scalar product it.n is then smaller than zero.

Literature 1. Bird RB, Stewart WE, Lightfoot EN (2002) Transport Phenomena. Sec. Ed., Wiley, New York 2. Fourier JB (1822) Theone analytique de la chaleur. Paris 3. Trajdos T (1971) Tensor analysis. Mathematics. Engineer's guide (in Polish). WNT, Warszawa


In this chapter, we will discuss mass and energy conservation equations while allowing for the fact that a solid can be mobile. Such situation occurs in processes of continual steel casting, during the transport of loose materials and in number of other processes.

2.1 Mass Balance Equation for a Solid that Moves at an Assigned Velocity Mass and energy balance will be calculated for a finite sector of a conductive area with a time-invariable volume V and surface A (Fig. 2.1). dA=ndA

v

A

Fig. 2.1. Mass flow with velocity w to the inside of volume V through surface A

Only a normal component of the mass flow penetrates through the external surface to the interior (2.1) where Wn

=-w·n.

(2.2)

One should note the scalar product sign wn = Iwllnlcoslp = W cos e = wn '

since

Inl = 1 (Fig. 2.2).

(2.3)

8


If mass flow is directed to the interior of the control volume V, it should have a positive value. Normal vector is a unitary vector directed to the outside. This means that for angles tp > 90 0 , when w is directed to the inside of the control volume, product w- n has a negative value. In order to obtain a positive value of w n product, when w is directed to the inside, one should add a minus sign in front of this product.

/ Fig. 2.2. The determination of a normal component wn of W vector

Mass balance conservation equation has the following form: (2.4)

~ fpdV=- fpw·ndA.

at v

(2.5)

A

Gauss-Ostrogradski equation is used to transform the right-hand-side

fF .ndA = fV . FdV,

(2.6)

v

A

where F is a vector of continual partial derivatives, while V is a Hamiltonian operator, formulated as

a

.e .a k - . v=l-+J-+

n

ax

8y

az

(2.7)

After the transformation of the right-hand-side of (2.5) with (2.6), one obtains

~ fpdV =- fV .(pw)dV.

at v

v

Since the control volume boundaries are not time-dependent, the time derivative can be inserted in place of an integral. Additionally, after moving the right-hand-side of the equation to the left side, one obtains

2.2 Inner Energy Balance Equation

f[OP +V"(PW)]dV=O.

v

at

9

(2.8)

Equation (2.8) is satisfied for every volume V, including a small volume. If V ~ 0, then one obtains from (2.8) the following:

Op +V'.(pw)=O.

(2.9)

at

This is a continuity equation written in a differential form. For Cartesian coordinates, it assumes the form

Op + o(PWx) + o(pwy) + o(pwz) = 0 . at ill ~ ill

(2.10)

Substantial derivative will be entered below in order to shorten the notation.

D a Dt at

a ax

a ay

a a az at

-=-+wx-+w -+wz-=-+w·v. Y

(2.11)

Such derivative shows how fast a parameter changes in time from the point of view of an observer, who moves along with the substance itself. Continuity (2.9) can be expressed then in the following form: Dp

-+p(v.w)=o.

(2.12)

Dt

2.2 Inner Energy Balance Equation Inner energy balance equation for the control volume has the following form:

~ fPUdV =- fpuw ·ndA -

at v

A

-fq ·ndA + ftlv dV + flPdV. A

v

fpp Dv dV v

Dt

(2.13)

v

Below, we will analyze the inner energy general balance equation for gases, liquids or solids, which move at w velocity, since heat conduction occurs not only in solids but also in gases and liquids. The integral can be found on the left-hand-side of the (2.13); it shows the inner energy changes that occur in time in volume V. The first term on the right-handside represents the inner energy flow, which moves to the control volume.

10


The second term represents reversible compression work of a medium contained within the control volume with respect to a unit of time. With consideration to the equation of continuity (2.12), the second expression on the right-hand-side (2.13) can be formulated in the following way:

J(

Dv JP Dp - pp-dV= --dV=p V·w)dV.

J

v

v P Dt

Dt

(2.14)

v

Reversible compression power is utilized for a density change of a medium p and contributes to a change in inner energy contained within the control volume V. The third expression on the right-hand-side of the equation is the conduction-transferred energy flow. The fourth expression represents the power of volumetric heat sources of density s.. which can be the function of position r, temperature T or time t. Dissipation function f/J is an irreversible power of internal friction forces, which influence the moving liquid particles. From Gauss-Ostrogradski theorem (2.6) applied to the first and third expression on the right-hand-side of the (2.13) and upon consideration of (2.14), one obtains

J[~(pu) + V'. (puw) + p(V'.w) + V'.q - iJv - (j)]dV = O. at

(2.15)

v

when V ~ 0, the (2.15) assumes the following form:

:t (pu) +

V' · (puw) = -V'.q -

p(V"w) + iJv + (j).

(2.16)

The left side of the (2.16) can be transformed in the following way:

a(pu) au ap a (upw )+ --+v.(puw)=p-+u-+-

at

at

at ax

x

+~( upwy )+~(upwz ) =

az

By

(2.17)

=u[op + o(PWx) + o(pwy) + O(PWz)]+

at

ax

ay

az

p au au au z -au) =U [a-+V· Du (pw )]+p-. +p ( -+wx-+w -+w at

ax

Y

ay

az

at

Dt


11

By allowing for the equation of continuity (2.9) in (2.17), one obtains

a(pu) + V (puw) = P Du & Dt 0

0

(2.18)

The first expression on the right-hand-side of (2.16), with respect to Fourier Law (1.6), can be written in the form

-V·4 =v .(AVT).

(2.19)

In order to transform the second expression on the right-hand-side of (2.16), the equation of continuity will be applied (2.12)

Dp +pV.w=O Dt '

(2.20)

1 Dp V·w=---.

(2.21)

pDp -pV·w=-P Dt

(2.22)

from which one obtains

P Dt

Term

can be transformed in the following way:

-pVow=pDp =pDp +p~(p)_p~(p)= P Dt P Dt Dt P Dt P (2.23)

=pDp +p(pDP _pDPJ_l _p~(pv)=Dp-p~(pv)o P Dt Dt Dt p2 Dt Dt Dt By allowing for (2.18), (2.19) and (2.23) in the inner energy balance equation (2.16) after the performed transformations, one has (2.24) where, i = u + pv is the specific enthalpy of a medium expressed in J/kg. Since the enthalpy differential of a substance i = i(p, 1) can be formulated [13, 16, 26] as

. (8i J dT+ (-8i)

dl= 8T

p

8p

dp=cpdT+v(l-pT)dp, T

(2.25)

12


the (2.24) can be written in the form PCp DT =V '(AVT)+iJv + prDp --», Dt Dt

(2.26)

where

f3-!(~) v

aT

p

__ ~(ap) aT p

(2.27) p

is the volumetric expansion coefficient. For liquids and solids, regarded as incompressible, one can assume that (2.28)

= RT,

In the case of a perfect gas, which fulfils Clapeyron equation pv the volumetric expansion coefficient amounts to

f3=~T

(2.29)

and energy balance equation (2.26) has the form pCp

DT =V.(AVT)+iJv+ Dt

Dp Dt

-»,

(2.30)

Equation (2.26) is a general energy balance equation for solids, gases or liquids, which move (flow) at w velocity. Thermophysical properties A, C and p may be position or temperature dependent. A body can also be anisotropic, when the thermal conductivity is direction-dependent. Rate of energy generation per unit volume of heat sources iJv can be a function of position, temperature and time. On the basis of the general equation (2.26), energy balance equations will be written in a Cartesian, cylindrical and spherical coordinate system. Term Dp/Dt will be omitted, since it is very small. It will be only taken into consideration in the cases of supersonic flows.

2.2.1 Energy Balance Equations in Three Basic Coordinate Systems Axes of a coordinate system will be selected in such a way that their directions will be the same as the general directions of an anisotropic body. Furthermore, we will present energy balance equations for different coordinate systems under the assumption that a liquid or a solid is incompressible.


13

Cartesian Coordinate System (Fig. 1.2a)

qx =- Axx aT ax '

aT qz· =- Azza;

°

(2.31)

ao ao a· ax ay az

-V'4 = v '(AVT)=-3..£_3L._~= (2.32)

=~(Axx ax aT)+~(A ax ay aT)+~(Azz ay az aT), az YY

D a -+w a -+w a -a . -=-+w Dt at xax ay zaz

(2.33)

y

By allowing for (2.32) and (2.33) in (2.30), one obtains a heat balance equation +w aT +w aT +w aT)= Pc (aT at xax ay zaz P

Y

(2.34)

-aT) +a( -aT) +-aT) +q. +(/J axa(AxXax ay- AYYay aza(AzZaz

=-

v

,

where the dissipation function is defined [20] by the following expression

(2.35)

+~(Owz + Ow )2+!(Owx+ Owz)2], y

2ayaz

2az

ax

where J.1 stands for a dynamic viscosity. If a body is immovable, then w = 0 and (/J = O. Thermophysical properties can be temperature or position-dependent. If we accept such an assumption (2.34) is simplified to a form pCp

aT aT)+iJ at =~(Axx ax aT)+~(Ay'y ax ay aT)+~(Azz ay az az

v•

(2.36)

14


Cylindrical Coordinate System (Fig. 1.2b)

. A aT qr =- rr&'

. --A ~ aT

q(} -

O(}

r

aB '

(2.37)

a( rar

aT) + ar

. 1 -v.q=V.(AVT)=-rArr -

(2.38)

D a a w(} a -a -=-+w Dt at -+--+w ar r aB az .

(2.39)

z

r

By allowing for (2.38) and (2.39) in (2.30), one obtains the equation below:

pc P

(aT +w aT + we aT +w aT)= at ar r aB az r

Z

(2.40)

a( rar

aT) +21 a (A(}(}aT) +a(A -aT) +qv. +([J, ar r aB aB aZ zz aZ

=1- - rArr -

where the dissipation function is defined by the following formula:

(2.41)

For an immobile solid w a form pCp

=0 and ([J =O. The

(2.40) is then simplified to

aT =!~(rArr aT)+~~(Aee aT)+~(Azz aT)+4v. at rar ar r aB aB az az

(2.42)

Spherical Coordinate System (Fig. 1.2c)

.

A aT

qr =- rr&'

4 rp

=-A rprp

_I_aT. r sin B arp ,

(2.43)


15

(2.44)

D a a we a wqy a -=-+Wr - + - - + - - - · Dt at

ar r ao rsinO arp

(2.45)

By allowing for (2.44) and (2.45) in (2.30), one obtains

a (2 er J+ 1 a (Aee sInO. otJ+ r ar ar r SIn 0ao ao

= 12 - r Arr -

+

2

1

• 2

2

•

a(A aT) + qv. + qyqy -

r SIn 0 arp

arp

(2.46)

(/J,

+--;-(_._1_ OwqJ + w + wectgO)2]+ r

sin e'

arp

r

(2.47)

1 . a wqy 1 Owe +sInO- - - + - - - 2 r oo( sin e' orp

[

sino)

For an immobile solid w = 0 and a form

2} ] .

(/J =

O. The (2.46) is then simplified to

16


et a (2 et J+ 2 1. a (AeeSlnO. et J+ at r ar ar r SInO ao ao

1 pCp-=zr Ar r

-

(2.48)

If a body is isotropic, then Arr = Aee = Alplp = A. Thermal conductivity A can be a function of temperature and position. Thermophysical properties of solids are listed in Appendix B at the back of the book.

2.3 Hyperbolic Heat Conduction Equation In the Subsect. 2.2, transient heat conduction equations were worked out for immobile solids with Cartesian (2.36), cylindrical (2.42) and spherical coordinates (2.48). These are a parabolic type of equations, based on Fourier Law, which assumes that heat diffuses at an infinitely fast rate. This means that any disturbances on the body's edges are immediately perceived in the form of temperature changes within the whole body volume. In the case of extremely rarefied gases, as well as helium and dialectric crystals at very low temperatures, the rate of heat flow propagation wg has a finite value. In such instances, the heat flux is formulated using the following constitutive equation [5,25]:

. aq AVT , q+rat=-

(2.49)

where t is the relaxation time. If one assumes that VT = 0, then (2.49) becomes a homogeneous differential equation of 1st order, whose solution is proportional to expression exp( -tl z), Relaxation time t is thus an equivalent of a time constant present in an expression that defines the temporal temperature flow of a body with a concentrated heat storage capacity. Energy balance equation (2.30) has in such a case the following form:

pc

ar at

n

-=-Y

p

..

.q+q .

(2.50)

v

If one assumes that p and cp are constant and differentiates equation with respect to time (2.50), one gets

a2T a· a· pc -=-V.~+~ 2 p

at

at at

(2.51)

2.4 Initial and Boundary Conditions

17

Divergence from both sides of (2.49) is formulated as V'q+TV, 8q

at

=-V.(AVT).

(2.52)

By allowing for (2.50) and (2.51) in (2.52), one obtains 2T

aT. -r [ pc a 2-a4v) D . ('JDT) -pc -+q - =-y /L.y , p

at

p

v

at

at

(2.53)

from where one gets, after assuming that thermal conductivity is constant 2T

aT a 2 1 (.qv+ra4v) , -+r--=aV T+-2 at at pcp at

(2.54)

2T

where a = AipCp' while V is a Laplace operator. Equation (2.54) is a partial hyperbolic equation, which describes the thermal wave propagation with the finite velocity (2.55) Relaxation time t is very small and for an alluminium, for example, it 11 6 comes to about 10- s, while for a liquid helium to about 10- s at extremely low temperatures. Since for a liquid helium with a temperature 2/s, close to an absolute zero, the diffusivity a amounts to 10 m the velocity of thermal wave propagation is (2.56) It can be seen, therefore, that the value of wq even in this case is large and for the majority of calculations done for transient heat conduction processes, it is assumed that r = 0 s, i.e. the velocity of heat propagation is infinitely large.

2.4 Initial and Boundary Conditions Transient heat conduction problems are initial-boundary problems for which one is required to assign appropriate initial and boundary conditions. Initial conditions, also called Cauchy conditions, are temperature values of a body at its initial moment to = 0 s.

18


T ( r, t )11=0 = To ( r ) ·

(2.57)

If temperature distribution is written in the form of a hyperbolic equation of heat conduction (2.54), then a initial derivative value must also be given.

aT( r,t) at t=O

(2.58)

where r is the positional vector of the analyzed point (a field vector in a given point). Symbol stands for the first temperature derivative with respect to time i = aT/at. In practise, one rarely makes use of the hyperbolic equation (2.54); therefore, only an assigned condition (2.57) is indispensible in order to determine transient temperature distribution. One can distinguish four basic types of boundary conditions [15, 27], which do not describe, nevertheless, all real conditions that occur in practise, such as body heating and cooling by radiation, the melting or freezing of bodies or complex heat transfer.

t

2.4.1 First Kind Boundary Conditions (Dirichlet Conditions) Temperature distribution on the edge of body A is assigned as follows (2.59) where fA is a positional vector of a point located on the body's surface. If temperature of the body surface, T(fA,t) is known from measurements taken, then the boundary conditions can be formulated as boundary conditions of the 1st order.

2.4.2 Second Kind Boundary Conditions von Neumann Conditions) (2.60) If x and y axes of a coordinate system are compatible with the main anisotropic axes, then the condition (2.60) assumes the form: (2.61)


19

where nx = cos(n, x), ny = cos(n, y) and nz = cos(n, z) are directional cosinuses of a normal to a surface. For isotropic bodies, condition (2.60) assumes the form (2.62) If a surface is thermally insulated, then

aTI an

==

o.

(2.63)

A

The boundary condition of 2nd kind is frequently set on the surface of radiated bodies, e.g. on the surface of boilers' radiant tubes. Surface temperature of the tubes, TA(rA,t) is much lower than the temperature of combustion gases Tsp in a furnace chamber and practically does not affect the heat flux transferred by the outer surface of the tubes. If the heat flux from a body surface is known from measurements taken, then the boundary condition of 2nd kind can be applied irrespectively of the type of heat transfer present on the body surface. Condition (2.62) is often set when solving steady-state and transient inverse heat conduction problems [9, 22, 23]. If thermophysical properties of a body c, p and A are temperature invariant, then the inverse problem becomes linear, thereby easier to solve, when a boundary condition of 1st or 2nd kind is applied on the body surface. 2.4.3 Third Kind Boundary Conditions The boundary condition of 3rd kind is also known as Robin boundary condition [15] or Newton law of cooling. Its heat penetration coefficient, also called heat transfer coefficient [28], expresses the intensity of convective heat exchange. Coefficient a is dependent on the type of heat exchange that occurs on a body's surface, the fluid type, and on the velocity and direction of the fluid flow with regard to body's surface. Heat transfer coefficient a is also frequently a function of surface temperature or of the difference between surface temperature TA and factor Tcz ' e.g. during boiling, condensation and natural convection.

- (AVT· n

t

=

a(rA,t,TA ) [ T( r A,t) -

T::zJ.

If a body is isotropic, then condition (2.64) is simplified to a form

(2.64)

20


) =a(TA-~z)' _(A aT an

(2.65)

A

The selected values of heat transfer coefficients are listed in Table 2.1. From the analysis of this table, it is evident that in the case of droplet condensation the surface temperature of a solid is close in value to a temperature of condensing vapour. In practise, the application of the 3rd kind boundary condition encounters difficulties with respect to the determination of spatial heat transfer coefficient changes and the medium's temperature at small flow velocity. If a liquid remains in a state of rest, then as a result of natural convection the medium moves alongside the solid's surface demonstrating, at the same time, significant temperature pulsations. Due to this reason, it is difficult to define the medium's temperature Tc/t). It also should be added that spatial-temporal changes in the heat transfer coefficient on the surface of a solid can be determined when a conjugated heat transfer problem in a liquid and solid is solved using a computerized fluid mechanics program, which consists of different CFD methods (abbr. Computer Fluid Dynamics).

Due to a shortage, however, of competent models, which would describe turbulent liquid dynamics, and experimentally-determined constants, the CFD-determined heat transfer coefficients can significantly digress from experimentally determined coefficients. Table 2.1. Approximate values of heat transfer coefficients Heat

'-'A"'.l.lUJ..lF;'-'

conditions

Forced convection

a Gases Oils Water metals

Free convection

Phase change

Gases Oils Water metals bubble boiling film boiling water vapour film condensation water vapour droplet condensation

10-500 50-1700 300-12000 1000-45000 5-30 10-350 100-1200 1000-7000 2000-50000 100-300 4000-17000

30000-120000

condensation of vapour of 500-2300


21

2.4.4 Fourth Kind Boundary Conditions The boundary conditions of 4th kind occur at the point where two bodysurfaces meet (CD and (2) Fig. 2.3). a)

b) T

T

n

n

A

A

Fig. 2.3. The course of temperature on the boundary of two adjoining bodies : a) ideal contact, b) contact resistance on the boundary

If contact is ideal, then the temperature of the two bodies is identical at the point of contact. Furthermore, heat flux becomes uniform. In the case of an ideal contact, the following equalities are valid (Fig. 2.3a):

(2.66)

lilA = T2 1A'

~ 8J; an

=

I

A

~ 8J; an

I

·

(2.67)

A

In reality, thermal resistance occurs at the point where two bodies meet and the bodies' temperatures at the point of contact are not the same (Fig.2.3b). Thermal resistance at the point of contact is characterized by means of the contact heat transfer coefficient a kt, which is defined as follows

(2.68) Coefficient a kt , which characterizes the contact resistance, mainly depends on the roughness of a surface and on the pressure force of both bodies. The contact resistance can be significantly reduced by polishing the two touching surfaces and by moistening them with a liquid, e.g. silicon, oil or petroleum jelly.

22


2.4.5 Non-Linear Boundary Conditions If a body surface is heated or cooled by radiation, then boundary condition is nonlinear (2.69) Temperatures of surface T IA and surroundings T, are expressed in degrees Kelvin. Symbol T, denotes the temperature of surrounding walls, which the body can "see." It is not a temperature of a medium Tcz directly located by the body surface, as it is in the case of convection. Shape coefficient F is the emissivity function of the body surface and its surroundings and of mutual configuration between the body and surroundings. If a surface area of a convex or flat body A is significantly smaller than the surface area of surroundings A r , then the heat flux on the body surface is only the emissivity function of the body surface e and temperatures TA and T;

~:IA =c:o-[(TIJ _~4] . 4

--1

(2.70)

Symbol a = 5.67.10- W/(m is a Stefan-Boltzmann constant. ) Thermal exchange by radiation plays a large role even in the case when surface temperatures of a body TIA are relatively low, e.g. thermal exchange by radiation in central heating radiators can amount to 40% of the total heat flow transferred by radiators. In reality, thermal exchange by convection and radiation occurs simultaneously on the surfaces of bodies treated with gases and, to a smaller degree, with liquids. Heat flux on the body surface is formulated as follows: 8

--1

2·K4

~:IA =a(TIA -~z)+()"F[(TIAr _~4J ·

If A 0 and 131 > 0 are assumed, and following that roots 132' 133, ••• are calculated using (15). Iterative process is continued until the following condition is met

If3n+l - f3n 1< e,

Exercise 6.29 Temperature Distribution and Efficiency

137

where e is the assigned tolerance of the calculation and equals e = 0.001. The results of fin efficiency calculation are presented in Fig. 6.34-6.37 for different values of k = r2/r1, 8 and M. L(}~-....---r----,r----....---r-----,r----t IIi

0.75

0.25 t--+--+--P~§.!I1

0.0

o.s

1.0

L5

2J)

25

3J) 3..5 1\1

Fig. 6.34. Efficiency of a fin with constant thickness and variable thermal conductivity for k = 1.6

to

- . . , - - - - r o - - . . , -_ _- - - , - -

___

'It 0,75

OJ)

0,5

1,0

1,5

2~O

2~5

3,0 3,5 1.11

Fig. 6.35. Efficiency of a circular fin with constant thickness and variable thermal conductivity for k = 2.0 1,0

1Jt 0,75 0,5

0,0

0,5

1,0

1,5

2,0

2,5

3,0

3,5

M

Fig. 6.36. Efficiency of a circular fin of constant thickness and variable thermal conductivity for k = 3.0

138

6 Heat Transfer Fundamentals

0,0

0,5

1,0

1,5

2,0

2,5

3,0

3,5

M

Fig. 6.37. Efficiency of a circular fin of constant thickness and variable thermal conductivity for k =4.0

From the comparisons presented in Table 6.4, it is evident that the given method for calculating fin efficiency is highly accurate. In paper [12], the method described above was also used to determine circular fin efficiency with position-dependent heat transfer coefficient a. Table 6.4. Efficiency 1Ji of a circular fin with constant thickness for k == 2; value 1Ji for e == 0 (constant thermal conductivity) calculated by means of the analytical formula ((10), Ex. 6.17) is given in brackets e

ParameterM 0

0.25

0.5

0.75

1.0

1.25

1.5

1.75

2.0

2.25

2.5

-0.6 1.0 0.8831 0.6915 0.5351 0.4217 0.3410 0.2829 0.2401 0.2078 0.1827 0.1628 -0.3 1.0 0.9241 0.7648 0.6095 0.4868 0.3959 0.3292 0.2795 0.2419 0.2126 0.1894 0.0 1.0 0.9445 0.8133 0.6674 0.5418 0.4440 0.3704 0.3149 0.2725 0.2395 0.2133 (1.0) (.9445) (0.8133)(0.6674) (0.5418)(0.4440) (0.3704)(0.3149) (0.2725) (0.2395) (.2133) 0.3 1.0 0.9565 0.8465 0.7128 0.5885 0.4867 0.4077 0.3473 0.3007 0.2643 0.2353 0.6 1.0 0.9642 0.8702 0.7486 0.6282 0.5247 0.4419 0.3772 0.3269 0.2874 0.2558

2.75 0.1468 0.1707 0.1921 (0.1921) 0.2119 0.2303

Literature 1. 2.

3.

4.

Bjorck A, Dahlquist G (1987) Numerical methods. PWN, Warsaw Brandt F (1985) Warmetibertragung in Dampferzeugem und Warmeaustauschern, FDBR Fachverband Damptkessel, Bchalter- und Rohrleitungsbau E.V. Vulkan Verlag, Essen Gnielinski V, Zukauskas A, Skrinska A (1992) Banks of plain and finned tubes. Chapter 2.5.3.Hewitt G. F.: Handbook of Heat Exchanger Design. Begell House, New York: 2.5.3-1-2.5.3-16 IMSL Math/Library (1994) Special Functions, Visual Numerics. Houston, Texas, USA.

Literature 5. 6. 7. 8. 9. 10. 11. 12.

13.

139

Janke E, Emde F, Losch F (1960) Tafeln hoherer Funktionen. B. G. Teubner, Stuttgart Lokshin VA, Peterson F, Schwarz AL (1988) Standard Methods of Hydraulic Design for Power Boilers. Hemisphere-Springer, Berlin-Washington MathCAD 7 Professional (1997). MathSoft Inc, Cambridge Massachusetts, USA Press WH, Teukolsky SA, Vetterling WT, Flannery BP (1996) Numerical Recipies in Fortran 77. Sec. Ed. Cambridge University Press Recknagel H, Sprenger E, Honmann W, Schramek ER (1994) Handbook, Heating and air conditioning, including refrigeration engineering and hot water supply. EWFE Schmidt ThE (1950) Die Warmeleistung von berippten Oberflachen. Abh. Deutsch. Kaltetechn, Verein. Nr. 4, C.F. Muller, Karlsruhe Schmidt ThE (1949) Heat transfer calculations for extended surfaces. Refig. Eng., Apr.: 351-357 Taler J, Przybylinski P (1982) Heat transfer by circular fins of variable conduction and non-uniform heat transfer coefficient. Chemical and Process Engineering 3, No 3-4:659-676 Weber RL (1994) Principles of Enhanced Heat Transfer. Wiley & Sons, New York

7 Two-Dimensional Steady-State Heat Conduction. Analytical Solutions

In order to solve steady-state heat conduction problems, we have employed in this chapter a well-known separation of variables method, which is an analytical method. We have derived formulas for two-dimensional temperature distribution in fins of an infinite and finite length and in the radiant tubes of boilers. A computational program was developed for determining temperature and heat flux in finite-length-fins.

Exercise 7.1 Temperature Distribution in an Infinitely Long Fin with Constant Thickness Determine temperature distribution in an infinitely long fin, shown in Fig. 7.1, by means of separation of variables method. Fin base temperature is 1;, while the temperature of a fin-surrounding medium is Tcz . Heat transfer coefficient a on the fin surface is constant.

y

x

a

Fig. 7.1. A diagram of an infinitely long fin

142


Solution Due to a symmetry of the temperature field, only an upper half of the fin will be examined here. Temperature distribution is described by the following differential equation

a2 T a2T

-+-==0

(1)

T(O,y)==~ ,

(2)

T(oo,y)==~z '

(3)

ax2

8y2

and boundary conditions

aT

-(x,o)==o,

(4)

-A-(x,w)=a[T(x,w)-J:z] · ay

(5)

8y

aT

Once dimensionless variables are introduced, such as • temperature (6)

• coordinates

X==~ , w

y==L , w

(7)

and Biot number o

aw A '

B 1==-

(8)

problem (1)-(5) can be written in the dimensionless form: (9)

e(o,Y)==I,

(10)

e( oo,y) == 0,

(11)

Exercise7.1 Temperature Distribution in an InfinitelyLong Fin... 143

8e(X 0)==0 8Y'

,

8e -(X,l)+ Bi- e(X,l) == O. 8Y

(12)

(13)

According to the separation of variables method, the solution has the form

e( X,Y) == U(X). V(Y).

(14)

By substituting (14) into (9), one obtains

U"V + UV" == 0 ,

(15)

which results in

U"

V"

2

(j=-V= u,

gdzie

(16)

From (16), one obtains two differential equations

2 d U _ 2U =0 dX 2 Ji ,

(17)

(18) Boundary conditions for (17) are obtained after substituting (14) into conditions (10) and (11)

uvlx=o == 1,

(19)

u(oo)==O.

(20)

Boundary conditions for function V(Y) are obtained by substituting solution (14) into boundary conditions (12) and (13)

~~(O)=O,

(21)

dV (l)+Bi 'V(l)=O.

(22)

dY

A general solution for (18) is the function

V == A COSJiY + BsinJiY.

(23)

144


Accounting for boundary condition (21), yelds B =O. Next, after substituting (23) into (22), characteristic equation is obtained - fi . sin fi

=0 ,

+ Bi . cos fi

(24)

which can be written in the form

1

(25)

ctg,u = Bi,u·

Equation (25) has an infinite number of roots fin > 0, n = 1,2, ..., which are the characteristic values of the problem in question. It is evident, therefore, that an infinite number of solutions exists for the Sturm-Liouville problem (18), (21), (22)

n=l, 2, ...

(26)

A general solution for (17) has the form

U = Ce'" + De-j.iX .

(27)

A great number of solutions U exist, which satisfy (17)

Un = Cnef1nX + Dn e- f1nX·

(28)

From the boundary condition (20), it is clear that C, = O. None of the solutions (14)

en =Un (X)Vn (Y)=An COS"rn Y·Dne-

f1nX

(29)

satisfy boundary condition (19). Once notation C, = AnDnis introduced, the solution will be searched for in the form of a linear combination of function (29), in a way that will satisfy heterogeneous boundary condition (10) (30) By substituting (30) into (10), one obtains 00

I c, COSfin Y =1.

(31)

n=l

After multiplying both sides of the equation by cos IlmY and by integrating them from 0 to 1, one obtains 1

1

n=lo

0

00

I JCn cos fin Y . cos fim YdY = Jcos fim YdY ·

(32)

Exercise 7.2 Temperature Distribution in a Straight Fin...

145

Since a set of characteristic functions is a set of orthogonal functions, which satisfy 1

Jcos,un Y. cos,um YdY = 0

°

therefore, for m

dla

msn,

(33)

=n from (32), one obtains 1

Jcos,un YdY Cn=-lO----

Jcos

2,un

(34)

YdY

°

hence, after integration one obtains Cn

2sinJln =---.--Jln + SIn Jln cos Jln

(35)

By substituting (35) into (30), a formula for temperature distribution has the form

Exercise 7.2 Temperature Distribution in a Straight Fin with Constant Thickness and Insulated Tip Determine two-dimensional steady-state temperature distribution in a straight fin with thickness 2w and length 1, made of a material with a constant thermal conductivity A. The fin is secured to a surface with a constant temperature Th • The fin tip is very well insulated. Lateral fin surfaces exchange heat with surroundings, at temperature Tez' by convection when heat transfer coefficient a remains constant (Fig. 7.2).

Solution Articles on the calculation of two-dimensional fin temperature fields are rather extensive in scope [2-9, 13, 14]. Fin temperature distribution is described by the heat conduction equation

a2r a2r

-+-=0

ax2

8y2

(1)

146


y

w

.. ""

....,....,....,....,.......,.......,~...-.,.......,.......,.....,.......,.

o

x

a

Fig. 7.2. A fin diagram with an assumed coordinate system

when boundary conditions are

T(O,y) = ~,

(2)

aT ax aT -(x,o)=o, -(l,y)=O,

(3)

(4)

8y

aT

-A-(x,w)=a[T(x,w)-Tcz ] 8y

•

(5)

After introducing dimensionless variables: • temperature

(6) • coordinates

X=~ ,

y=L,

w

(7)

w

and the Biot number aw B1 = o

A'

(8)

problem (1)-(5) can be written in the dimensionless form:

a2e a2e

-+ 2 -=0

ax ay2

(9)

Exercise 7.2 Temperature Distribution in a Straight Fin... 147

e(o,Y)=I,

(10)

ae(L Y)=O ax' ,

(11)

ae(X 0)=0

(12)

aY'

,

ae(X,l) + Bi ·e( X,l) = o.

ay

(13)

In accordance with the separation of variables method, the solution of problems (9)-(13) is searched for in the form

e(x,Y) = u(x). V(Y).

(14)

Function V(Y) has the same form as it does in Ex. 7.1. Function V(X) is, much like in Ex. 7.1, determined from equation 2

a u2 _ 2U =0 ax Jl ,

(15)

when boundary conditions are

UV\x=o = 1,

au ax

-(L) = 0, where L = l/w.

(16) (17)

The solution for (15), which satisfies condition (17), is the function U=Ccosh,u(L-X).

(18)

Since the characteristic equation (25) from Ex. 7.1 has an infinite number of positive elements Jln , an infinite number of functions exist (19) which satisfy (15) and boundary condition (17). The solution of problems (9)-(13) will be searched for in the form

e(x,Y)= funvn = fC ncosh zz, (L-X) -ccs u.)'. n=l n=l

(20)

Constant en in expression (20) is determined from the heterogeneous boundary condition (10), which yields the following result: 00

L en cosh Jln L . cos Jln Y =1 . n=l

(21)

148


After multiplying both sides of the equation by cos ing dY from 0 to 1, one gets 1

1

n=lo

0

00

fimY

and after integrat-

L f Cn cosh fin L . cos fin Y . cos fim Y = fcos fim Y dY .

(22)

From orthogonal condition of function cos finY' COSfimY ((33), Ex. 7.1), one obtains 1

fCosfin Yd Y

C; cosh finL =

0-----.;.1

[cos'

(23)

fin Yd Y

o

hence

c n

=

2sin,un cosh fin L (fin + sin fin cos fin)

(24) .

en

By substituting constant formulated in (24) into expression (20), temperature distribution is formulated as

e(x Y)=2I ,

sin,un x + sin fin cos fin )

n=l cosh fin L (fin

xcosh zz, (L -

(25)

X). cos finY'

where fin are positive elements of the characteristic transcendental equation (26)

Exercise 7.3 Calculating Temperature Distribution and Heat Flux in a Straight Fin with Constant Thickness and Insulated Tip Calculate temperature distribution in a fin on the basis of a formula derived in Ex. 7.2. Calculate fin temperature in points shown in Fig. 7.3. Also calculate heat flux at the fin base in points (0,0) and (O,w). Determine a formula for averaged temperature and heat flux across the fin thickness. Compare mean temperature values across the entire fin length and heat flux at the fin base with one-dimensional solution. Assume the following values for the calculation: w = 0.003m, 1 = 0.024 m, a = 100 W/(rrt·K), T; = 95°C, Tcz = 20°C, Ax =0.003 m, A = 50 W/(m·K).

Exercise 7.3 Calculating Temperature Distribution and Heat Flux

149

y

-T. cz

a 82 2

~

4

6

8

10

3

5

7

9

N

X

a

-r: Fig. 7.3. A fin diagram with marked nodes, in which temperature is calculated

Solution On the basis of (25) from Ex. 7.2, temperature distribution T (X,Y) will be calculated from formula (1)

where

e;.( ( X,Y ) -_ 2~ LJ ( n=l JL

sinJln

)

n + sin JL n . cos JL n

coshJln (L - X) COSJlnY, cosh JLn L

(2)

where: X = x/w, Y = y/w, Bi = aw/A. Elements of the characteristic equation

1

ctgz, = Bi,u

(3)

will be determined by means of the interval halving method; one should note, however, that the infinite element JL n lies in an interval between Jln,min = (n - l)Jr and JLn,max = (n - 1/2) Jr. Values JLn,max are characteristic values of the Strum-Liouville problem in an instance when Bi ~ 00, i.e. when constant temperature is assigned on the fin surface. Mean temperature across the fin thickness is determined from formula 1w

i (x) = -

W

J[I:z + (T

b -

o

t; )()] dy ,

(4)

150

7 Two-Dimensional Steady-StateHeat Conduction. AnalyticalSolutions

from where, one obtains

Heat flux in the direction of x axis comes to

q

=_).

aT = 2).(1;, -~z)f

sinhlln(L-X) x

n=l (f.1n + sin f.1n . cos f.1n)

w

ax

x

Ilnsinlln

cosh f.1nL

(6)

x cos f.1n Y .

Mean heat flux value across the fin thickness is the function of x coordinate -:-

1w

f

.(

)d

2A(4 - ~z) L ~ sinf.1n .J.

qx=-qxx,yy= wow

x

sinh f.1n(L -

n=l (f.1n + SIn f.1n . cos f.1n )

x

X) .

coshf.1nL

(7)

SInf.1n .

Fin temperature distribution TId' determined under the assumption that temperature decrease within the fin thickness is negligibly small, is expressed by function (Ex. 6.15)

J;d (x ) = t; + (1;, - ~J

coshm(l-x)

(8)

hi' cos m

where m=~a/Aw. In the given case m=

50

= 12.90994

11m .

100·0.003 In the case of the one-dimensional solution, heat flux is formulated as

. ( )_

qld

at; _(

x --A--dx

4 -~z ) Am sinh m (I- x ) coshml

.

(9)

Allowing that Bi = aw/A = 100·0.003/50 = 0.006, the first ten elements of the characteristic equation (3) were determined:

~!~

i~j

J&- . !&-

.~.

~

0.0774 13.1435 ;6.2841 19.4254 112.5668115.7083118.8499121.9914!25.1330128.2745


151

Next, the elements were applied to (2). Temperature T (x, y) in nodes shown in Fig. 7.3 was calculated by means of the FORTRAN program, which comes with this exercise. Proper values j.1 n were calculated by means of the sub-program presented in paper [1]. Mean temperature distribution T(x) and temperature TId (x) were also calculated. Heat flux was calculated at two points: B 1 and B 2 (Fig. 7.3). Mean heat flux

4x at the fin base (X = 0) was calculated on the basis of (7). For

comparison purposes 4Id was also calculated for x = 0 by means of (9). Temperature calculation results are shown in Table 7.1. Table 7.1. Calculation results x[m]

Node no.

Temperature [OC]

Node no.

Temperature [OC]

0 0.003 0.006 0.009 0.012 0.015 0.018 0.021 0.024

B]

95.00 92.09 89.55 87.42 85.70 84.37 83.42 82.86 82.67

B2

94.99 91.88 89.34 87.22 85.50 84.18 83.23 82.67 82.48

1 3 5 7 9 11 13 15

2 4 6 8 10 12 14 16

n., B2 1,2 3,4 5,6 7,8 9, 10 11, 12 13, 14 16

95.00 92.02 89.48 87.35 85.63 84.30 83.36 82.80 82.61

95.00 92.02 89.47 87.34 85.62 84.29 83.34 82.78 82.59

Calculated heat flux measures: • at point B 1

4x (0,0) == 49764 W/m

2 ,

• at point B 2

4x(0,w)==66646 W/m 2 , • mean heat flux at the fin base 4x

4x (0) == 53253 W/m

2

,

• heat flux 4Id at the fin base

4Id(O)==53341 W/m

2 •

From the analysis of the obtained results, it is evident that there is a small temperature decrease across the fin thickness. Also, heat flux 4x varies in points B 1 and B2 • A good accuracy of results is evident in

T (x) and TId (x),

152


qx (0) and qld (0), i.e. between the mean values across the fin thickness

obtained under the assumption that fin temperature field is two-dimensional and between values determined under the assumption that temperature decrease across the fin thickness is negligibly small, i.e. temperature and heat flux are only the function of x coordinate. Program for Calculating Two-Dimensional Fin Temperature Field program fin dimension eigen(50) open(unit=l,file='fin.in') open(unit=2,file='fin.out') read(l,*)ne,bi read(l,*)t_cz,t_b,dlug,w,s_lam,s_alfa write(2,' (a) I) &"CALCULATING TWO-DIMENSIONAL FIN TEMPERATURE FIELD" write(2,' (/a)') "DATA ENTERED" write(2,'(a,ilO)') "ne =",ne write(2,' (a,elO.5) ') "Biot number=",bi write(2,'(a,elO.5,a)') "t_cz =",t_cz," [C]" write(2,'(a,elO.5,a)') "t_b =",t_b," [C]" write(2,'(a,elO.5,a)') "dlug =",dlug," [m] " write(2, (a,elO.5,a)') "w =" ,w," [m]" write (2, (a, elO. 5, a) ') "lambda =", s_lam," [W/mK]" write(2,'(a,elO.5,a)') "alfa =",s_alfa," [W/m2K]" write (2, , (la, i3, a) ') "CALCULATION OF FIRST", ne, &" EQUATION ELEMENTS X*TAN(X)=BI" call equation_elements (bi,ne,eigen) write(2,' (/a) ')"CALCULATED EQUATION ELEMENTS" write(2, , (a)') "Lp mi " do i=l,ne write(2, (i2,5x,ell.6)') i,eigen(i) enddo write (2, , (/a) I) "CALCULATED TEMPERATURE [C]" write(2,' (a) ')" x[m] T(x,Bl) T(x,B2) T_sr(x) T_ld(x)" x=O. do i=l,lO write(2,' (f5.3,4(3x,elO.5)) I)X, & temperature(x,O.,t_cz,t_b,dlug,w,ne,eigen), & temperature(x,w,t_cz,t_b,dlug,w,ne,eigen), & temperature_sr(x,t_cz,t_b,dlug,w,ne,eigen), & temperature_ld(x,t_cz,t_b,dlug,w,s_lam,s_alfa) x=x+dlug/float(8) enddo write(2,' (/a)') "CALCULATED HEAT FLUX [W/m2]" write(2,' (a,elO.5) ') "~x(O,O)=", &value_q(O.,O.,t_cz,t_b,dlug,w,ne,eigen,s_lam) I

I

I


153

write(2, (a/elO.5) ') "CI-x(O/w)="/ &value_q(O./w/t_cz/t_b/dlug/w/ne/eigen/s_lam) write(2/' (a,elO.5) ') "CI-x_sr(O)=", &value_CI-sr(O./t_cz/t_b/dlug/w/ne/eigen/s_lam) write(2/' (a/elO.5)') "CI-x_ld(O)=", &value_CI-ld(O.,t_cz/t_b/dlug/w/s_lam/s_alfa) end program fin I

function value_CI-ld(x/t_cz/t_b/dlug/w/s_lam/s_alfa) s_m=sqrt(s_alfa/s_lam/w) value_CI-ld=(t_b-t_cz)*s_lam*s_m*sinh(s_m* &(dlug-x))/cosh(s_m*dlug) end function function value_q(x/y/t_cz/t_b/dlug/w/ne/eigen/s_lam) dimension eigen(*) teta=O. x_b=x/w y_b=y/w dlug_b=dlug/w do i=l/ne s=eigen(i) teta=teta+s*sin(s) *sinh(s* (dlug_b-x b)) &*cos(s*y_b)/(s+sin(s)*cos(s))/cosh(s*dlug_b) enddo value_q=2.*(t_b-t_cz)*s_lam*teta/w end function function value_CI-sr(x/t_cz/t_b/dlug/w/ne/eigen/s_lam) dimension eigen(*) teta=O. x_b=x/w dlug_b=dlug/w do i=l/ne s=eigen(i) teta=teta+sin(s)*sinh(s*(dlug_b-x_b))*sin(s)/ &(s+sin(s)*cos(s))/cosh(s*dlug_b) enddo value_CI-sr=2.*(t_b-t_cz)*s_lam*teta/w end function function temperature_ld(x/t_cz/t_b/dlug/w/s_lam/s_alfa) s_m=sqrt(s_alfa/s_lam/w) temperature_ld=t_cz+(t_b-t_cz)*cosh(s_m*(dlug-x)) &/cosh(s_m*dlug) end function function temperature_sr(x/t_cz/t_b/dlug,w,ne/eigen)

154

7 Two-Dimensional Steady-State Heat Conduction. Analytical Solutions dimension eigen(*) teta=O. x_b=x/w dlug_b=dlug/w do i=l,ne s=eigen(i) teta=teta+sin(s)*cosh(s*(dlug_b-x_b))*sin(s)/ &s/(s+sin(s)*cos(s))/cosh(s*dlug_b) enddo temperature_sr=t_cz+(t_b-t_cz)*2.*teta end function function temperature(x,y,t_cz,t_b,dlug,w,ne,eigen) dimension eigen(*) teta=O. x_b=x/w y_b=y/w dlug_b=dlug/w do i=l,ne s=eigen(i) teta=teta+sin(s)*cosh(s*(dlug_b-x_b))*cos(s*y_b)/ &(s+sin(s)*cos(s))/cosh(s*dlug_b) enddo temperature=t_cz+(t_b-t_cz)*2.*teta end function

c c c c

procedure calculates elements of characteristic eq. x*tan(x)=bi where bi is Biot number, ne calculated element quantity, eigen vector with recorded calculated elements subroutine equation_elements (bi,ne,eigen) dimension eigen(*) pi=3.141592654 do i=l,ne xi=(float(i)-l.)*pi xf=pi*(float(i)-.5) do while (abs(xf-xi) .ge.5.E-06) xm=(xi+xf)/2. y=xm*sin(xm)/cos(xm)-bi if (y.lt.O.) then xi=xm else xf=xm endif enddo eigen(i)=xm enddo return

Exercise 7.3 Calculating Temperature Distribution and Heat Flux end data(fin.in) 10 0.006 20. 95. 0.024 0.003 50. 100. results(fin.out) CALCULATING TWO-DIMENSIONAL FIN TEMPERATURE FIELD DATA ENTERED ne 10 Biot number=.60000E-02 t_cz =.20000E+02 [C] =.95000E+02 [C] =.24000E-01 [m] w =.30000E-02 [m] lambda =.50000E+02 [W/mK] alfa =.10000E+03 [W/m2K] CALCULATION OF FIRST 10 EQUATION ELEMENTS X*TAN(X)=BI CALCULATED EQUATION ELEMENTS Lp mi 1 .773851E-01 2 .314350E+01 3 .628414E+01 4 .942542E+01 5 .125668E+02 6 .157083E+02 7 .188499E+02 8 .219914E+02 9 .251330E+02 10 .282745E+02 CALCULATED TEMPERATURE [C] x[m] T(x,B1) T(x,B2) .000 .95000E+02 .94990E+02 .003 .92095E+02 .91887E+02 .006 .89554E+02 .89346E+02 .009 .87426E+02 .87224E+02 .012 .85702E+02 .85506E+02 .015 .843 72E+02 .84180E+02 .018 .83428E+02 .83238E+02 .021 .82863E+02 .82675E+02 .024 .82676E+02 .82488E+02 .027 .82863E+02 .82675E+02 CALCULATED HEAT FLUX [W/m2] ~x(O,0)=.49764E+05

~x(O,w)=.66646E+05 ~x_sr(O)=.53253E+05 ~x_1d(O)=.53341E+05

T_sr(x) .95000E+02 .92026E+02 .89485E+02 .87359E+02 .85637E+02 .84308E+02 .83365E+02 .82801E+02 .82613E+02 .82801E+02

T_1d(x) .95000E+02 .92021E+02 .89475E+02 .87346E+02 .85621E+02 .84290E+02 .83345E+02 .82781E+02 .82593E+02 .82781E+02

155

156


Exercise 7.4 Temperature Distribution in a Radiant Tube of a Boiler Determine formula for temperature distribution in the boiler's radiant tube (Fig. 7.4) by means of the separation of variables method. Assuming that heat flux qm (thermal load of the water-wall) transferred by the water-wall is known (calculated with reference to a wall regarded as a plane), as well as the temperature of a medium that flows inside the tube Tcz and heat transfer coefficient a on an inner surface of the tube, determine temperature field in the function of coordinates rand rp. Also calculate the inner and outer surface tube temperature for angle rp = 0 and rp = Jr rad; use the following values for the calculation: • • • •

outer surface tube radius r z = 0.019 m, inner surface tube radius r w = 0.015 m, scale of radiant tube spacing s = 0.042 m, thermal load of the water-wall s; = 300000 W/m ~

• heat transfer coefficient on the inner surface of the tube 2·K), a= 15 000 W/(m • temperature of a medium Tc: = 330°C, • heat conduction coefficient of the steel which the tube is made of A =45 W/(m·K). combustion chamber

/

Fig. 7.4. A diagram of a radiant tube spacing in a combustion chamber

Exercise 7.4 Temperature Distribution in a Radiant Tube of a Boiler

157

Heat flux on the outer surface of the tube is expressed by function [12]

q( cp) = qm (0.3649 + 0.4777 coscp+ 0.1574cos2cp)

.

(1)

Solution Tube temperature distribution is expressed by heat conduction equation (2)


A

~~Ir=r,

=

1]0 +

~I]n cos( nqJ) ,

A aTI =aTI ' 8r r=r r-r;

(3)

(4)

w

where T is the temperature excess of the tube t; above the temperature of the medium Sez' i.e. T = t;- Sez· In conformity with the separation of variables method, the solution is searched for in the form

T(r,cp)=U(r) 'V(cp).

(5)

By substituting (5), one obtains equation

r 2U"V + rU'V + UV" = 0 .

(6)

After a division of (6) by UVand the separation of variables, one obtains V"

U

V

(7)

Since rand cp are independent variables, equality (7) occurs only when its both sides are equal to the same constant. If the constant were negative, the solution V( cp) would then contain exponential functions, which would unable one to satisfy periodic boundary condition (3) written in the Fourier series form. Separated constant, therefore, must be either a positive inte2 gral number or zero. If one assumes that both sides of (7) are equal to n , one obtains

158


(8)

n=O, 1, ...

(9)

In the case of a circular-symmetrical load only

qo *-

0, whereas

qi = q2 =... = O. For n = 0, the solution of (8) and (9) has the form U(r)=~+B~lnr

(10)

v(rp ) = c; + D~rp .

(11)

and

Due to the circular-symmetrical load D~ be written in the form

U (r)V ( rp ) = Av +

= 0,

e; In r,

the product U(r) V(rp) can

n=O,

(12)

where, Av = ~e', Bo = B~e~. For n ~ 1, the solution of (8)-(9) has the forms

U(r) = A'n r n + B'n r- n'

(13)

V ( rp) = e~ cos vup + D~ sin nip .

(14)

Due to the symmetry of tube heating (condition (3)) with respect to the plane, which is perpendicular to the water-wall and which crosses the tube axis, constant D~ = O. Product U(r)V(rp) can be written in the form n~l,

(15)

where, en = A~ e~ and D; = B~e~ . Expression (5), which describes the distribution of excess temperature in the tube, has the form

T(r,tp) =

Av + BoIn r +

f( Cnrn+ Dnr-n)cosntp .

(16)

n=I

After substituting (16) into boundary conditions (3) and (4), one can determine constants, which can be written after transformation in the following form: L1 = .l~

J

40Arz (_1 -lnr Bi w'

Exercise 7.4 Temperature Distribution in a Radiant Tube of a Boiler

B

159

= qorz

A'

o

where, U = r Ir .Bi = a rIA. Since in thisWexercise, the heat flux on the outer surface of the pipe is defined by (1), then

40 = 0.36494m' 41 = 0.47774m' 42 = 0.15744m' and

43 = 44 = ... = 0, It is easy to calculate tube temperature, when only 2 terms are accounted for in the series (16). Once the following is calculated

u=!.£..= 0.019 Bi

=1.2667,

0.015

rw

= arw = 15000·0.015 = 5.0 A

45

and substituted into solution (16), one obtains

T(rz'O) = 52.28°C, T(rw'O) = 23.53°C, T(rz,Jr) = 2.31 °C, T (rw ' Jr) = 1.04°C. These are temperatures above the medium's temperature. Corresponding pipe temperatures are:

((rz'O) = ~z + T(rz'O) = 330 + 52.28 = 382.28°C, ((rw'O) = ~z + T(rw'O) = 330 + 23.53 = 353.53°C,

160


s(rz,n-) = ~z + T(rz,n-) = 330+ 2.31 = 332.31 °C, S(rw,n-) = J:z + T(rw,n-) = 330 + 1.04 = 331.04°C. It is evident that temperature S(rz'O) is the maximum temperature across the whole cross-section of the tube. Provided that this temperature is known, one can correctly chose the right type of steel for the radiant tube of a boiler.

Literature 1. 2. 3. 4. 5. 6.

7. 8. 9. 10.

11.

12.

13. 14.

15.

Becker M (1986) Heat Transfer. A Modern Approach. Plenum Press, New York Gdula SJ et. al. (1984) Heat conduction. Group work. PWN, Warsaw: 134-138 Irey RK (1968) Errors in the one-dimensional fin solution. Transactions of the ASME, 1. Heat Transfer 90: 175-178 Lau W, Tan CW (1973) Errors in one-dimensional heat transfer analyses in straight and annular fins. Transactions of the ASME, 1. Heat Transfer 95: 549-551 Look DC (1995) Fin on pipe (insulated tip): minimum conditions for fin to be beneficial. Heat Transfer Engineering 16, No.3: 65-75 Look DCJr, Kang HS (1991) Effects of variation in root temperature on heat lost from a thermally non-symmetric fin. Int. 1. Heat Mass Transfer 34, No. 4/5: 10591065 Look DCJr (1999) Fin (on pipe) effectiveness: one dimensional and two dimensional. Transactions of the ASME, J. Heat Transfer 121: 227-230 Look DCJr (1988) Two-dimensional fin performance: Bi (top surface) > Bi (bottom surface). Transactions of the ASME, 1. Heat Transfer 110: 780-782 Ma SW, Behbahani AI, Tsuei YG (1991) Two-dimensional rectangular fin with variable heat transfer coefficient. Int. 1. Heat and Mass Transfer 34, No 1: 79-85 Mlynarski F, Taler J (1979) Analytische Untersuchung der Temperatur - und Spannungsverteilung in strahlungsbeheizten Kesselrohren unter der Beriicksichtigung der wasserseitigen Ablagerungen. VGB Kraftwerkstechnik 5: 440-447 Taler J, Kulesza L (1982) Calculating temperature field in finned, bimetallic and homogenous screen pipes with a layer of residue on an inner surface. Archives of Power Engineering 1: 3-23 Taler J (1980) Weighed residues method and its application for temperature field calculation in boilers' elements. Monograph 14, Pub. Krakow University of Technology, Krakow (1999) The Heat Transfer Problem Solver, Problem 3-5. Research and Education Association. Piscataway, New Jersey USA: 142-145 Unal HC (1988) The effect of the boundary condition at a fin tip on the performance of the fin with and without internal heat generation. Int. 1. Heat Mass Transfer 31, No.7: 1483-1496 Kraus AD, Aziz A, Welty J (2001) Extended Surface Heat Transfer. Wiley & Sons, New York

8 Analytical Approximation Methods. Integral Heat Balance Method

In this chapter an integral heat balance method, which is an approximate method [1-8], was applied to solve various engineering problems. It ensures fast obtaining of an approximated solution, marked by simplicity of form. Accuracy of approximated solution is higher when heat flow is significantly larger in one direction than it is in others. For this reason, integral heat balance method is recommended for determining steady-state temperature fields, which are not much different from one-dimensional steady-state temperature field.

Exercise 8.1 Temperature Distribution within a Rectangular Cross-Section of a Bar Determine temperature distribution in an infinitely long bar of a rectangular cross-section, heated by thermal sources with constant power density 4v. Bar temperature T, (Fig. 8.1) at perimeter is constant. Determine temperature distribution by means of integral heat balance method.

Solution Temperature distribution T(x,y) is expressed by heat conduction equation 2 2 a r a r 4v -+-=--

ax 2

8y2

A

(1)

and by boundary conditions (2) (3)

162


Fig. 8.1. A bar of a rectangular cross-section

In accordance with integral heat balance method, temperature distribution will be approximated by the following function, which satisfies boundary conditions and temperature field symmetry conditions with respect to axis x andy:

If we assume in (4) that x = 0 and y = 0, then T (0,0) = Tmax • Constant Tmax , which is present in function (4) and approximates real temperature distribution, is determined through an integration of (1) within an entire rectangle area: -b/2 ~ x ~ b/2, -h/2 ~ y ~ h/2. Approximate temperature distribution (4) is replaced by an integral

f f (8-8xT+ -8T+qv-Jdxdy==O

h/2

b/2

2

2

2

-h/2 -b/2

Oy2

(5)

A,

and after transformations, one obtains (6)

Solution (6) is a good approximation of an accurate solution, when b » h or b « h. In both cases, temperature distribution is almost onedimensional. The lowest accuracy is obtained in the case of a square crosssection, when b = h. Then difference (Tmax - Tb ) determined from (6) is by 27% larger than a difference obtained from an exact analytical solution.

Exercise 8.2 Temperature Distribution in an Infinitely Long Fin

163

Exercise 8.2 Temperature Distribution in an Infinitely Long Fin of Constant Thickness Determine temperature distribution in a fin depicted in Fig. 8.2. Fin base temperature T, is constant. Determine temperature distribution by means of approximate method: integral heat balance method. y

o

x

Fig. 8.2. Two-dimensional steady-state temperature field in an infinitely long fin

Solution Temperature distribution is expressed by a differential equation of steadystate heat conduction (1)

and by boundary conditions

T( x, ± w) == Too' Once new variable is introduced be written in the following form:

e =T -

a2e a2e

-2-+--2

ax

ay

T( oo,y) == Too .

(2)

Too, (1) and conditions (2) can

==0,

(3)

where emax= Tmax- Too. Approximate temperature distribution will be searched for in a form (5)

164


Function (5) is selected in such a way that it satisfies boundary condition e(y, ±w) =0 and the temperature field symmetry condition with respect to axis x, i.e.

ae 8y

=0.

(6)

y=o

In accordance with heat balance method, heat conduction equation (3) is integrated within the area under analysis (due to a symmetry of temperature field after division in two parts)

2e If (aax + a2e) dxdy = 0 . 8y

woo

--2

--2

(7)

o0


11[(

w

2

-l )U" -2U] dxdy = 0 ,

o0

from which, after integration in the direction of y-axis, we have (8)

Applying the boundary conditions (4) in (8), one obtains 3U"

i[%w

-2wU]dx=O,

(9)

which yields differential equation

U"-~U=O. w

(10)

Boundary conditions for U result from the first and third boundary condition in (4). From the first condition, one obtains (11)

from which, after simple transformations, one has

U(O)= em;" . w

(12)

Exercise 8.3 Temperature Distribution in a Boiler's Water-Wall Tube

165

From third boundary condition in (4), one obtains a second boundary condition for U (x) (13) U(oo)=o. Solution of (10) has the form (14)

By substituting (14) into condition (12) and (13), one is able to determine constant C1 and C2 (15)

Function Vex) is given by

U(x) = e;;x exp (

-../3:).

(16)

By allowing for (16) in (5), the expression for approximate temperature distribution has the form (17)

Exercise 8.3 Determining Temperature Distribution in a Boiler's Water-Wall Tube by Means of Functional Correction Method Solved the problem formulated in Ex. 7.4 using functional correction method.

Solution First we will briefly characterize functional correction method [6], which is also an analytical approximate method. If heat flux is much larger in one direction than it is in another, then temperature field resembles onedimensional temperature field. Functional correction method is very effective for determining such temperature fields. A typical example of such problem is the conduction of heat in a fin, in which the flow is much larger in the direction of x axis than it is in the direction of y axis (Ex. 7.2, Fig. 7.2). Heat conduction equation

166

8 AnalyticalApproximation Methods. Integral Heat Balance Method

a2T a2T

-+-=0

(1)

aX2 8y2

will be approximated by differential equation, in which derivative will be approximated by mean value within the fin thickness

a

2T/a

y2

(2) where

1 wa 2T

f(x) = - - f-dY 2 w o ax

.

(3)

As follows from (2), it has been assumed that second derivative is a function of coordinate x and doesn't depend, on coordinate y. Temperature distribution is determined in the following way. Once (2) is integrated twice, one obtains

r(x, Y) =!2 l f (x) + CIY+ C2 ,

a

2T/a

y2

(4)

where C1 and C2 are constants, which are determined from appropriate boundary conditions in the direction of y axis. Once (4) is substituted into (3) and all mathematical operations carried out, one obtains ordinary differential equation of 2nd order for j(x). After integrating this equation in the presence of appropriate boundary conditions at the base and tip of a fin, one obtains temperature distribution in the fin. In order to determine temperature distribution in a water-wall tube, whose temperature field is expressed by equation

!~(raTJ+~2a r =0 2

rar ar

(5)

r aqJ2


/) aTI = qo. + ~. LJqn cosrup, ar r-r.

(6)

/1.,-

n=l

A aTI

(7)

ar r-r: =aTI r-r; ' (r,qJ)

above a temperawhere T = S- Scz is excess temperature of tube S ture of medium Scz' functional correction method will be applied. In a water-wall tube heat flux in circumferential direction is much smaller than in

Exercise 8.3 Temperature Distribution in a Boiler's Water-Wall Tube

167

radial direction. One could determine, therefore, tube temperature distribution under the assumption that temperature is only a function of a single variable r, while ignore tube heat flow in the circumferential direction. Maximum tube temperature Tm ax = T (rz'O) determined in such way is to large, since an outflow of heat from frontal part of the pipe to its cooler rear side is not taken into consideration. One can make more accurate determination of temperature distribution in a tube by means of functional correction method, according to which (5) can be substituted by approximate equation

a( aT)

1 - r - = !(q;) -

r ar

ar

,

(8)

where

2

f(rp) =

1

z

r

2

2

rz - rw

a2 r

f-Z-2 rdr. r aq;

(9)

rw

Once (9) is integrated twice, one obtains

T(r,rp) =.!- f( tp)r 2 + C1 ln r + C2 4

(10)

•

After constants C1 and C2 are determined from boundary condition (6) and (7) and substituted into (10), one obtains

(11)

= arw , q( rp) = qo + fqn cos ntp .

where Bi

A

n=l

Once (11) is substituted into (9) and all computational operations conducted, the following differential equation is obtained 2

! 2 --2- m ! = d

dip

where u = m'

2m

2

rz

-

2 2

(1--In r r 1 )~. u+--.Inu L...Jqnn cos rup , z

2

rw 2 A

2

z

A Bz

(12)

n=l

r.lr; , 4Bi(u

2-1)

=----:-----:---------:--------2 2 2 2 -Bi(u

-1) + 2Biu

1n u + 4( u

-1 )lnu + 2Bilnu .

(13)

168


Boundary conditions for function symmetry conditions

et acp q>=O

=

f (cp)

result from temperature field

et

(14)

acp q>=7r

from which follows that

af

af

acp q>=O

acp q>=7r

(15)

=0.

The solution of (12) with boundary conditions (15) is function

f(cp)=

2m

2

rz

2 rw

-

(1--In < u+--.lnu r. 1 )L

4nn2 2 2 cosne: n=l m + n

2

2

2A

00

A Bi

(16)

From (11), (13) and (16), tube temperature was calculated on an outer and inner tube surface for angles tp = 0 and tp = 1r as a function of Biot number Bi. The obtained approximate values were compared with values, which were calculated by means of analytical formula (Ex. 7.4, (16)). The comparison is presented in Table 8.1. Calculation results were given in a dimensionless form e =

TA = (( - (cz) A as a function of Biot number Bi = a rIA. From the 4m rz w comparison of results presented in Table 8.1, one can conclude that the accuracy of approximate method is very good. Also, in the functional correction method computational formulas have a simpler form than they do in the analytical method.

4m rz

Table 8.1. Comparison of temperature e = T A /s; r, calculated by means of approximate formula (11) and analytical formula ((16), Ex. 7.4); in top rows values e were given, calculated by means of exact analytical formulas, while in bottom rows approximate values were given T = 383.333°C. 3

How the calculation results are going to change, if measurement values contain a measurement error I1.T = + 1.0°C i.e.

ft = T

1+I1.T

I> T

= 333.333

3+I1.T=

+ 1.0 = 334.333°C,

383.333 + 1.0 =384.333°C.

-2

~

• 1

• ./1 350°C

-

350°C

3

•

~x

4

• ~. 350°C 350°C

Fig. 11.4. Inverse heat conduction problem; temperature it is measured in node 1, while the unknown temperature at point TB lies on the body edge

Solution In general, temperatures in volume nodes or finite elements are formulated by the equation system

200

11 Solving Steady-State Heat Conduction Problems

= bi a21I;. + a22I; + a23I; + + a2nT:z = b2

allI;. + a12I; + a13T; +

+ aInT:z

(1)

Parameters that appear in the boundary conditions are expressed by the terms on the right side of the system, i.e. in vector b = tb; b2 , ••• , bn)T, while i = 1, ..., n, J. = 1, ..., n, i.e. the coefficient matrix A is coefficients a.., IJ known. If the equation system (1) is written in the matrix form

AT=b,

(2)

where

A=

all

a12

a13

«;

a 2I

a22 a23

«;

anI

«:

ann

«;

I;.

, T=

bi

T

b , b= 2

t;

bn

2

(3)

then the solution of the system (2) has the form

T

==

A-1b,

(4)

where A-I is the inverse matrix to A. Once we determine the inverse matrix

(5)

we can determine node temperatures from (4)

I;. = cll bi + c12b2 + c13b3 + + cInbn I; = C2Ibi + C22b2 + C23b3 + + c2nbn (6)

If temperature! in node i is known from measurements taken, while

Exercise 11.3 A Two-Dimensional Inverse Steady-State Heat Conduction

201

coefficient bj is unknown, then from the equality condition of measured temperature ~ and calculated T, , one obtains f.=

ji

T.l '

(7)

from where, after accounting for (6), one is able to determine coefficient b. ]

b. = ~ -cilb! -ci2b2 -Ci3b3 - ... -Ci,j_1bj_! -ci,j+!bj+! - ... -cinbn . } c.. I,}

(8)

If the measurement data contains an error, then (8) assumes the form

b. )

= (~+dT)-Cilb! -ci2b2 -Ci3b3 -",-ci,j_!bj_! -ci,j+!bj+! -oo.-cinbn . c.. I,}

Should the problem formulated in this exercise appear (Fig. 11.4), then the balance equation system has the following form 4~

-T2

-~

-~

+41; -1; =550

=TB +350

-T2 +41; -T4 =850 -~

-1; +4T4 =750

Hence, the coefficient matrix has the form

A=

4

-1

o

-1

-1

4

-1

0

o

-1

4

-1

-1

0

-1

4

Inverse matrix, determined by means of MATINV program (see Appendix E), is

C=A- I =

Cll

c12

c13

cln

0.292

0.083

0.042

0.083

C2 1

C22

C23

«;

0.083

0.292

0.083

0.042

0.042

0.083

0.292

0.083

0.083

0.042

0.083

0.292

cnl

cn2

(10)

then boundary conditions (3) and (4) can be correspondingly written in the form (11)

(12)

Exercise 11.10 Description of FEM Based on Galerkin Method

241

where qn is the component value of the normal heat flux. One also assumes that the body thickness in the direction perpendicular to the plane of the diagram is of 1m. Boundary problem (1)-(4) was formulated for the whole region Q. In FEM, Galerkin method is first formulated for a single element Qe. It is assumed that three types of boundary conditions are assigned, as they are for the whole region, on the boundary of a single element. One needs to apply such a formulation to elements adjacent to body boundary (Fig. 11.11). It is not necessary, however, to consider boundary conditions for elements, which lie inside the body. Temperature distribution inside the element Q e is approximated by function

r (x,y) = tT/ ·N; (x,y) = [N e ]{r},

(13)

j=l

where n is the number of nodes in the element, ~e - temperature inj-node and ~e(x, y) the shape function (interpolation function). Galerkin method will be used to determine an approximate temperature ~e in nodes, j = 1, ..., n.

a ( A are] +qv.] N,e(x,y)dxdy=O. f -a ( Ax-are] +ax ay Oy y -

sr [ax

(14)

Green theorem will be applied in order to transform (14):

f -aG- -aF] dxdy = P(Fdx + Gdx) . sr ( ax ay r:

(15)

Integration on the boundary T" is anti-clockwise.

If one assumes that

F = -Ay are N~ ay 1

an

d G = AX are lN~'

ax

(16)

then on the basis of (15), one obtains

f[~(AX ar Nie]+~(A ar Nt]]dXdY = ax ay Yay

Qeax

= fN~ ( re

1

are]

ar e

(17)

-A -dX+A -dlJ a . y~,

vy

x

X

.r

Once the left-hand-side of (17) is transformed, the equation can be written in the form

242


e

i I[~(AX ar)+~(Ay I(Axor sr ax ax ay ar)]NtdXdY=ay sr ax aN ax + are _ aN~) are) . +AYayay _ , dxdv « re' IN.e(are -AYay -dX+Axax -dlJ

(18)

J

J

By substituting (18) into (14), one has

I(Ax or aNt + Ayor aNt) dxdy = INt q.dxdy + ax ax ay ay sr are are). +INt -Ay-dx+Ax-dy ( re ay ax sr

(19)

Because of (Fig. 11.12)

-dx = ds · sin cp = n ds , dy

(20)

= as-coup = n ds

(21)

and on the basis of (10), the expression in the brackets in the curvilinear integral in (19) can be transformed in the following way:

are are arn dS+A -arn ds=-q·n=q . . ds. -AYay -dX+A -dlJ=A x xax yayy xax J

n

(22)

Hence, from the above and the boundary conditions (11) and (12) in (19), one gets

e I(Axor aNi +Ayor aNt)dXdY= INtqdxdy « INt4B ds+ sr ax ax ay ay sr r; (23) +

I Nt a (t: - r: )ds. r;

After substituting (13) into (23), one gets

aN~ aN~ aN~ aN~ J e_ fA Lr +A Lr/dxdy fN;etivdxdy+ y_ ' x[ ax ir ax ay ay sr l

n

n

J

J

j

j=l

j=l

n

+fNttiB ds- fN;eaLT/N;ds+ fNieaJ;,zds. r;

r;

j=l

r;

>

(24)

Exercise 11.10 Description of FEM Based on Galerkin Method

243

Equation (24) for i-node can be written in the form n

I( K:,ij + K~,ij ). T/ = f;,i + t; + t; '

(25)

j=l

3

- Ax~07'.I -Ay~OT.J J

(

vy

ex

y

2

o

x

Fig. 11.12. A diagram with a calculation of a curvilinear integral on the element's perimeter (in an anti-clockwise direction)

where K" .. == C,l]

f1 fle

[

aN~

a lA Te _:I._Vi _ _ J

x

aX aX

+1

aN~)

alATe _:I._Vi _ _ J

Y~, vy

«: = faNtN;ds,

ay

dxd Y,

(26)

(27)

r:

f

e

f;,i = qvNi dxdy ,

(28)

fle

(29)

244


and

J

I'e = a Tcz Ned is.

J a,i

(30)

r;

If in (14), and by that in (25) ~e is assumed to be the shape function for the consecutive nodes of a finite element, then one obtains for a given element a system of n equations, which can be written in the form

([K:] + [K~ ]){r} ={f;} + {~e} + {f:},

(31)

where matrix coefficient and elements of column vectors are expressed by e (26)-(30), while vector {T} has the form {T} = [ T/, ... , Tn ] , where n is the number of nodes in an element. In contrast to other exercises where bold type designates matrixes and column vectors, the traditional notation used in FEM is preserved in (31). [ ] stands for a matrix or row vector, e while { } a column vector. Matrix [Ke ] is called stiffnes or conductivity e matrix. Matrix [Ke ] is symmetrical, since K:,ij = K:,ji' Equation (31) forms the basis of FEM for (1). Equation system (31) is frequently written in a slightly different form. Once (13) is substituted into (7), temperature gradient vector can be written in the form

8Ne _ 8N_2e 8x 8x

__ 1

{s} = _ aN_1e _ aN_2e 8y

8y

e __ n

8N 8x

{r} .

(32)

8y

If we denote by [B] the matrix in the square bracket:

8Ne _ 8N_2e 8x 8x [B]= 8N_2e 8N_1e _ _ 8y 8y __ 1

8N: 8x 8N: 8y

(33)

Then {g} can be expressed in a shortened form

{g} =[ Be ] {r }.

(34)

e

Conductivity matrix [K e ] can be written then in the form (35)

Exercise 11.11 Determining Conductivity Matrix

245

The remaining matrixes and column vectors present in (31) can be expressed in the following way:

[K=J= fa[Ner[NeJds, r;

{f~ }= f 4v [N Qe

{~e} =

e

r

(36)

dxdy ,

f4B[ Ner sr r qe

r

{f:}= f aTcz [ N ds, e

r~

(37)

Nt Ne

,while n is the number of nodes in an element.

2

Exercise 11.11 Determining Conductivity Matrix for a Rectangular and Triangular Element e Determine conductivity matrix [K e ] for a rectangular and triangular element.

Solution Equation (26) from Ex. 11.10 and formulas for shape functions shown in Ex. 11.9. will be used to calculate the elements of a conductivity matrix. a) Conductivity matrix [Keel for a finite rectangular element e

Matrix elements [Ke ] are expressed by (26) in Ex. 11.10

K:,ij

=

BNei _ BN~J + A _ BN_ie _ BN~) fAx _ J dxdy. y ( Qe Bx Bx By By

(1)

246


Only two matrix elements will be calculated from (19) in Ex. 11.9 for the

K:,ll

shape functions

and

K:,12. Let x, y be local coordinates.

After determining derivatives

aNt =__ 1 (I- LJ

ax

2b

and

2a

aNt = __ 1 (1-~J 8y

2a

(2)

2b

and

aN; =_1(I- L

ax

element

K:,ll

2b

2a

J and aN; =_~ , 8y 4ab

will be calculated first

x: = f [A, aNt aNt + A, aNt aNt) dxd c,ll

(3)

ne

x

aX aX

=Ax2a [2b 1 ( l- L o 0 4b 2a

f f-2

y~, vy

ay

Y

=

J2] 1 ( 1-X J2 dx]dy= dx dy+A,y 2af [2bf-2 0

0

4a

2b

(4)

Ax a Ay b =--+-- . 3 b 3 a Element K:,12 is calculated in a similar way:

x: = f [A, aNt aN; + A, aNt aN; )dXd = c,12 ne x aX aX aY aY Y y

J2]

2

Y dx dy+A 2a [2b 1 [ x -x-) dx]dy= =-Ax2a [2b 1 ( 1-y o 0 4b 2a 0 0 8a b 2b

f f-2

Ax a

f f-2

(5)

Ay b

=---+-- . 3 b 6 a e

Also the remaining elements of the conductivity matrix [K c ] can be determined in a similar way, namely

Exercise 11.11 Determining Conductivity Matrix

2 1 -1 -2 2 -2 -1 1 Ay b 1 2 -2 -1 [Kce]=Ax6 ~b -2 2 1 -1 +--1 1 2 -2 1 6 a -1 -2 2 1 -1 -2 2 -2 -1 1 2

247

(6)

b) Conductivity matrix [K'] for a finite triangular element

Matrix [B] for a triangular element is formulated as

aNe aNe aNe ax ax ax 1 [be [B e]= aN e aN; aN e =2A e c; ay 8y 8y __ 1

__ 1

__ 2

__ 3

__ 3

be2 ce 2

b;]e '

(7)

C3

e

where A is the surface area of a triangle, while coefficients bie , c; , i = 1, 2, 3, are expressed by formulas in (8), Ex. 11.9. Since the coefficients in matrix [Be] are constants and Ax and Ay are material constants independent of position and temperature inside the element, the conductivity matrix can be easily determined, since

[K;]= J[BeJ[Ae][BeJdxdy=[BeJ[Ae][Be] fdxdy sr

sr

or (8)

Once (7) is substituted into (8) and the appropriate operations carried out, one obtains

(btt [Ke]=~ c 4A e

«« btb;

««

(ctt c7 c; c7 c; A ee (b;t b;b; +_x_ (c;t e e e 4A cece c;c; (c;t b;b; (b;t btb;

e

C1C2

C2C3

. (9)

1 3

It can easily verify that the same results are obtained when calculating matrix coefficient with (1). When a body is isotropic, i.e. Axe = Axe=A\ the e conductivity matrix [K e ] for a triangle expressed by (9) can be written in a simpler form, by introducing the notation shown in Fig. 11.13.

248


y

c

l __- - - - - -__~....I------..

(0,0)

x

b

Fig. 11.13. Triangular finite element

On the basis of formulas (8) from Ex. 11.9 and the notations from Fig. e 11.13, (9) for Axe = Axe = A can be written in the form

+(C-b)2

b( c - b)

- c(c- b) b( c -b)

-cb

d'

[K;J= 4~e

-d

2

. (10)

b2

-cb

In a case when a triangle is rectangular in shape (Fig. 11.14), conductivity matrix assumes the form d d

b

[K;J= ~e ~ o

b d b -+b d b

d

o b d b d

(11)

Exercise 11.12 Determining Matrix [K(/] in Terms of Convective Boundary

249

c=b

y

Ae =

b

lL:.Jl 2

3

o ...- - - - -..........~--'-------.... 2

x

Fig. 11.14. Finite element in a rectangular triangle form

Exercise 11.12 Determining Matrix [Ka"l in Terms of Convective Boundary Conditions for a Rectangular and Triangular Element e

Determine matrix [K a ] for a rectangular and triangular element.

Solution e

Matrix [K a ] present in (25) [Ex. 11.10], whose coefficients are expressed by (27) [Ex. 11.10], arises from 3rd order boundary conditions assigned on e the boundary of an element. Matrix [K a ] can be also determined by means of (36) from Ex. 11.10. Coefficients K~ ,ljii will be calculated by means of (27) from Ex. 11.10

f

K~,ij = aNtN;ds . r;

(1)

The determination of integrals in FEM is discussed, among others, in articles [4, 6]. a) Rectangular finite element

If convective heat transfer is assigned on all sides of an element with a e heat transfer coefficient a, then matrix [Ka ] is formulated as

250


(N:f NtN; Nt N; NtN: NtN; (N;f N;N; N;N: [K;J = fa Nt N; N;N; (N;f N;N: NtN: N;N: N;N: (N:f

ds.

(2)

r~

In practice, convective heat transfer is usually set on one or two element sides, which constitute a fragment of a body boundary. If convective heat transfer takes place on the side 1-2 of a rectangular element (Fig. 11.15), then in (2) one should assume thatN3 = N 4 = O. Equation (2) assumes the form

(N:f Nt N; [K;J= fa NtN; (N;f 2b 0

Since ds (3) are

0 0 0 0 ds.

0

0

0 0

0

0

0 0

(3)

=dx and on the basis of (19) from Ex. 11.9, individual integrals in e)2 12 fb( N dX = 2b = L 1 3 3'

2

(4)

o

where L 12 is the length of the side 1-2 of the element in question. y

3

4 "

\j

N

S

Qe

~

!l (~

('1

,

-..J

Fe

L]2

=2b

'\

a

2

X

Tez Fig. 11.15. Convective heat transfer is prescribed on the boundary 1-2 of a rectangular element

Exercise 11.12 Determining Matrix [K(e] in Terms of Convective Boundary

251

Furthermore, once the following is determined

fob N N dx = 2b6 = L6

2

e

1

e 2

12

(5)

and (6)

matrix (3) assumes the form 2

= aL [KeJ a 6

12

1 0 0

1 2 0 0

0 0 0 0 000 0

(7)

Similar results are obtained for the remaining sides of the element

o

0 0 0

= aL23 0 2 [KeJ a 601 o 0

1 0

2 0 0 0

(8)

000 0

= aL34 0 0 [KeJ a 600

= aL [KeJ a 6

41

0 0 2

1

001

2

200

1

0

0

0 0

000 0

(9)

(10)

100 2 where L 23, L 34 , L 4 1 are the lengths of the sides on which the convective heat transfer takes place. b) Triangular finite element e

For a triangular element, matrix [K a ] has the form

252

11 Solving Steady-StateHeat ConductionProblems

[K=J = r;fa

(Ntr Nt N; Nt N; N;Nt (N;r N;N; N;Nt N;N; (N;r

ds.

(11)

The above matrix refers to a case when convective heat transfer takes place on all three sides of a triangular element. When heat transfer occurs e= only on the side 1-2, one assumes in (11) that N3 0, while after integration, one has

[K= J= a~12

210 1 2 0 .

(12)

000 Formulas for the remaining sides are obtained in a similar way

[K= J= a~23

000 0 2

1

(13)

012

(14)

where L 12 , L 23, L 31 are the respective side lengths of the triangular element. When calculating curvilinear integrals, present in (11), for a triangular element, needed in order to determine (12)-(14), (1) was used: (15) It is easy to calculate the integrals in (11) by means of (15); e.g. to calculate integral ~2

2

f(Nn ds,

o

in (15), one assumes that m = 2, n = 0, hence

f(N~)2ds=L o

1

12

2!O! =L ~=LI2 . (2 + 0 + 1)! 12 3 . 2 ·1 3

Exercise 11.13 Determining Vector {f~} with Respect

253

Exercise 11.13 Determining Vector {fae } with Respect toVolumetric and Point Heat Sources in a Rectangular and Triangular Element Determine vector {fQe} for a rectangular and triangular element, when unit heat source power is constant within the area of the element and constant for a point heat source. y 4

.Ji

3

.*

l

~qv

...,. 1

2

Xo

x

Fig. 11.16. Point heat source inside a rectangular element

Solution Vector components {fQe} will be calculated according to (28) from Ex. 11.10

i; = f4v N tdxdy .

(1)

Qe

a) Rectangular element

If power density of a heat source is constant, it is easy to calculate

2a(2b ) f;,; = J IqvN;edx dy; hence, after substituting into (19) from Ex. 11.9, one obtains

{f;,;} (2)

254


1

1 1

{f~} = iJv:e

1

== qah

1

(3)

1 1

1

where A e is the surface area of an element, equal to 4ab. It follows from (3) that 1/4 of total body heat flow is allotted to every node in a tetragonal element. In the case of the point heat source (Fig. 11.16), (1) assumes the form

iJv == iJ: t5 ( x- Xo)t5(y - Yo),

(4)

4:

where [W/m] is the heat flow emitted at point (xo' Yo)' with respect to a unit of length as the heat source is infinitely long in the direction perpendicular to the diagram plane. Function t5 is a Dirac delta, which approaches infinity at point (xo' Yo); at the remaining points, however, it equals zero. By substituting (4) into (1), one has

Nt (xo,Yo)

{f~ } = iJ:

N; (xo' Yo ) N; (xo,Yo) . N: (xo,Yo)

(5)

b) Triangular element

If density

4v

is constant, then from (1), one obtains

f;,i == 4v

f Ntdxdy.

n

(6)

e

In order to calculate the integral on the surface of a triangular element, a formula from reference [4] will be used here:

f(Nn1(N;f (N;fdA = ne

l!m!n! ,2Ae (l+m+n+2).

o

(7)

Since in the given case m = 0, n = 0, l = 1, then from (6), one has

f/Q,i = iJvAe 3· Therefore, vector {fQe} has the form

(8)

Exercise 11.13 Determining Vector {f~ } with Respect

255

1

{f;}= qv:e

1 .

(9)

1

It follows from (9) that 1/3 of the total heat flow in an element is allotted to every node in that element. In the case of point heat source, vector {fQe} has the form

{f;}=q:

Nt (xo,Yo) N;(xo'yo) · N; (xo,Yo)

(10)

Equations (5) and (10) refer to a case when the point heat source is located inside an element. When a heat source is located in a node common to several elements per unit of length can be divided (Fig. 11.17), then source power

q:

among individual elements proportionally to angle qJ at the tip of a given element. For a triangular element, vector {fQe} has the form

(11)

where angle tp is expressed in radians.

Fig. 11.17. Point heat source in a node common to several elements

In practice, the location of a heat source is of no great significance, since in the global equation system, with the heat balance equations for individual nodes, total power is present in this equation of a node, which has a point heat source inside.

q:

256


Exercise 11.14 Determining Vectors {fqe} and {fae} with Respect to Boundary Conditions of 2nd and 3rd Kind on the Boundary of a Rectangular or Triangular Element Determine vectors ment.

e and {fa } for a finite rectangular and triangular ele-

~e}

Solution e Elements of column vectors {te} and {fa } are determined from (29) and q (30), Ex. 11.10 (1)

J; = f a~zNie ds ,

(2)

r; therefore, from almost identical integrals. If we assume that qB = aTcz in the first integral, then we obtain (2). This is why only vector ~e} will be determined below. a) Finite rectangular element

If heat flux is given on the boundary 1-2 of a finite element (Fig. 11.18) with thickness 1, then vector {te} is formulated as q

(3)

Since also N; =N; =0 on the side 1-2, (3) assumes the form

Nt (x, 0)

f:

{ } =qB

2fb N;(x,O) 0 0 dx ,

o where shape functions

Nt

and

N;

are expressed by (19), in Ex. 11.9.

(4)

e} Exercise 11.14 Determining Vectors {fq and {fuel

257

y

rqe / x

2

Fig. 11.18. Rectangular element heated by heat flux

qB

Once the integrals are calculated 2b

2b(

e

X

J

X 2 2b

dx=x-f N 1 (x , O)dx= f 1-2b 4b

L12 =b=-

2 '

0 0 0 2b

2b

2 2b

x x Ne(x O)dx = -dx =2' 2b 4b

f

f

0 0 0

L

= b =--l1:-

2 '

(5)

(6)

vector {te} can be written in the form q 1

{/qe} = qB~12 ~

(7)

o It is evident from the analysis of (7) that the term qB L12/2 for node no. 1 will appear on the right -hand-side of the (25), Ex. 11.10, as it will for node no. 2. This means that half of the heat, which flows through the lateral surface of an element with length L 12 and thickness 1, flows to node no. 1. The second half flows to node no. 2. Vector {te} can be calculated in a similar q way when the heat inflows into the element through surfaces 2-3, 3-4 and 4-1; one then obtains, respectively

o

{/qe} = qB~23 ~ o

(8)

258


o ·L 0 {re} = 2 u ' qB

34

(9)

J q

1

1 ·L

{ fe } = ~ 2 q

0

.

0

(10)

1 If the heat flow at density qB inflows through all lateral surfaces of an element (Fig. 11.18), then vectors (7)-(10) should be added; hence L12 +L41 L12 + L 23

(11)

L 23 + L34 L34 + L41

From the analysis of (11), it is evident that the term qB (£12+ £41)/2 for node no. 1 will appear on the right-hand-side of an algebraic equation, term qB (L 12+ L32)/2 for node no. 2 on the right-hand-side of the equation, and so on. The above is, therefore, the same procedure for calculating heat balance in nodes as the one, which is used in the control volume method. b) Finite triangular element

To calculate curvilinear integral (1), we will use formula L

fNjmCs)NJCs)ds =L ( o

,

,

m.n. ) .

(12)

m+n+l !

Vector

Nt N;

{~e} = f qB[ NeT ds =qB f ds , r: r: N;

(13)

with a heat flux set on the surface 1-2 is calculated under the assumption that N; = 0 and m = 1, n =0 in (12). Once the integrals are calculated

Exercise 11.15 Methods for Building Global Equation System in FEM

f N ds = L o

Lt2

e

1

1'0' L .. = --R 12 (1 + 0 + I)! 2'

L

Lt2

f Neds = --R o 2 2'

259

(14)

(15)

vector {fe} assumes the form q 1

{f

e

q }

=

qB;2 1

(16)

o If a heat flow with density qB is assigned on the surface 2-3 or 3-1, then the corresponding vectors have the form

{~e} = qB~23

o 1

(17)

1

{~e} = qB~31

1 0

.

(18)

1 When heating a triangular element on all sides, an appropriate vector is obtained as a result of adding vectors (16)-(18)

. {L +L {~e} = q; L'2 +L 23 12

31

}

.

(19)

L23 + L31

As in the case of a rectangular element, a heat flow, which inflows through half of the surfaces that pass through a given node, occurs on the right-hand-side of an algebraic equation when the equation is being formulated for a given node.

Exercise 11.15 Methods for Building Global Equation System in FEM Describe the way global equation system is created using the finite element method by summing up

260


a) equation systems obtained for individual finite elements [Method I],

b) algebraic equations obtained for different elements that share, nevertheless, a common node (as an analogy to finite volume method) [Method II]. Are the temperature continuity conditions and heat flux conditions satisfied on the boundary between elements?

Solution e

a) In order to create a global equation system, conductivity matrix [Ke ]

and the matrix that comes from the assigned 3rd kind boundary conditions e [Ka ] , derived for individual elements, must be summated, i.e. N

[K] = I([ K; J+ [ K~ J)

(1)

e=l

That includes the summation of vectors {fQe} , right-hand-side of the (31) in Ex. 11.10

~e},

e}, {fa present on the

(2)

(3)

and

(4) e=l

where N is the finite elements integral number, which the entire analyzed region was divided to. The global equation system for temperature in element nodes has the form (5)

where {T} is the column vector of size N, which comprises of unknown temperatures in element nodes. Next, one has to account for parameters present in the boundary conditions in the above created global equation system (5). The method for creating matrix [K], which is sparse, should be discussed in greater detail, since only some of the coefficients present in it are


261

other than zero. It is assumed that the flat region is divided into triangular elements (Fig. 11.19). e

d g

a

Fig. 11.19. A division of a flat region into finite triangular elements; element numbers and global node numbers are marked: CD-@ - finite element numbers, a-g - global node numbers

If element CD lies inside the analyzed region, thereby [K a ] can be disre1 1 garded, then matrix [K ] = [K c ] for the first element (Fig. 11.20) can be written in the following way: 1

a

(1) (2) (3)

KIll

K~l K~l

b

c

K:2 K:3 K~2 K~3 K~2 K~3

(6)

(1) (2) (3) If global node numbers of a triangular element are marked as G, b, and c, while local node numbers as (I), (2), (3), then one can see that coefficient 1 1 1 K aa corresponds to coefficient in matrix [K ] (6), coefficient K bc cor1 responds to coefficient K 23 , etc. When creating a matrix of coefficients [K] according to (1), one should be guided by global indexes, i.e. one should add coefficient K eaa that occurs in the matrix of element ® to coefficient 1 K aa that occurs in the conductivity matrix of element CD. Coefficients that have the same global indexes in conductivity matrixes of other elements are added together. Such common coefficients appear in conductivity matrixes of elements, which share a common node, e.g. in the case of elements in Fig. 11.19, the node common to six elements is node c.

r;

262


c

Numeration of nodes in elementno. CD Global node number

Local node number

a

(1) (2) (3)

b c

a

Fig. 11.20. A diagram of global (a, b and c) and local (1), (2), (3») node numeration in a triangular element

A global equation system for node temperatures can be created in another way, which resembles the way heat balance equations are developed using the control volume method. One can also create control volume in FEM around node c (Fig. 11.19), common to surrounding elements, by linking centers of gravity of triangular elements with the midpoints of triangle sides (Fig. 11.21). The equation number equal to the number of nodes in an element is assigned to every element. There are three equations in the case of a triangular element. When creating a global equation for node c (Fig. 11.19), only those equations are considered in which the shape function was selected as a weight function in the Galerkin method at point c. For element CD when local nodes are positioned as shown in Fig. 11.20, the third equation is the equation in question; it results from the application 1 of Galerkin method when weight coefficient equals N 3 (X, y).

i

o g

control volume assigned to node c

centerof gravity of triangular element midpoint of triangle side

a

Fig. 11.21. Control volume in FEM with a region divided into triangular elements; linear functions interpolate temperature distribution inside the element

If similar local node numeration is assumed for the remaining elements shown in Fig. 11.19, then we must account for the third equation in every equation system for a given element, since in every element local node (3)


263

e

corresponds to node c. In Galerkin method, function N3 (x,y) plays a role of a weight function for element ®. b) The second method for creating global equation system, based on the formulation of an appropriate equation for a given node, indicates that there is a close relationship between FEM and the control (finite) volume method. The following conditions should be retained when aggregating (summating) elements (Fig. 11.22): • continuity of temperature field, including boundaries between elements; • continuity of heat flow, also on the boundary between elements. The first condition is satisfied in FEM; the second condition, however, is not completely satisfied. On the boundary between elements, the following temperature continuity takes place

1;1 = 1;2 = T:t and (7)

The above indexes (7) are the element numbers. Temperature equality on the boundary between elements follows from the equation of temperature in nodes and linear character of temperature distribution inside the elements. 4

3

2

Fig. 11.22. Global and local numeration of nodes in finite elements

In agreement with (29), Ex. 11.10, the equality of integrals takes place on the boundary between elements:

f q~N~ds =- f q~N12ds , Lh3

f q~N~ds =- f q~N~ds . Lh3

(8)

43 (9)

43

Therefore, only in the case of very small elements, when the side common to both elements is very short in length, the heat flux equality is ensured on the boundary where two elements meet. Furthermore, heat flux inside an

264


element is constant when temperature distribution is interpolated inside the element by linear functions. Therefore, heat flux step-change occurs at the point of contact of two elements. At such point, there is also no continuity among the first derivatives of function rex, y). This lack of continuity at the point of contact between elements negatively affects the accuracy of solution. In order to determine heat flux at a given point in an analyzed region or to calculate heat flow transmitted by a body boundary, the region should be divided into very small elements, so that the accuracy of the determined heat flux values is satisfactory.

Exercise 11.16 Determining Temperature Distribution in a Square Cross-Section of an Infinitely Long Rod by Means of FEM, in which the Global Equation System is Constructed using Method I (from Ex. 11.15) Determine temperature distribution in a square cross-section of an infinitely long rod (Fig. 11.23). Upper and lower surfaces are thermally insulated. Left vertical surface is heated by a heat flow whose density is qB = 200 000 W/m 2 , while the surface on the opposite side is cooled by water at temperature

a

= 1000 W/(m

~z

= 20 e 0

with a heat transfer coefficient equal to

2·K).

Thermal conductivity of the rod's material Ax = Ay = 50 W/(m·K). The length of the side within the square cross-section of the rod is a = 2 em.

a = 1OOOW/(m2 -K)

Ax =Ay = 50 W/(m K) 0

a=2cm

Fig. 11.23. Cross-section of an infinitely long rod

Exercise 11.16 Temperature Distribution in a Square Cross-Section

265

Solution Temperature field will be treated as two-dimensional. Cross-section of the rod will be divided into four elements. Local and global node numeration is given in Fig. 11.24. and Table 11.2. .v

3 4 __- - - - - - - -__- - y o

8

, 1

SUB =1

TIME"'l TEJ.IP RSYS=O

(AVG)

Powerv.r:aphics EFACET=l

G

TEMP RSYS=O

H

POf4etGraphics EFACET=1

AVRES=Mat SMN =102. 505 SM)( =150.747

A B C D

x

AVRE5"'11at SflN "'107.399 SRX =186.649 A -i u .ecz B =120.606 C =129.413 D ""136.219

G

=105.185 =110.545

""115. 90S =121. 266

E

r

"'126.626 e131. 986

G

=137.346

H I

=142.706 =148.067

(AVG)

F E D

C B /' '~~.

+--

E

=147.024

F G

..155.83 "'164.635

H I

=173.44 =182.246

....,

x A

Fig. 11.36. Layout of isotherms on the pin surface: (a) cylindrical pin, (b) conical pin

306


'b

'b

where = 0.003 m for cylindrical pin, = 0.004 m for conical pin and r =0.0015 m. For cylindrical pin = 8.892 W, while for conical pin =

o:

o;

8.456 W. As one can see, the shape of the conical pin is a very advantageous, since in spite of the fact that the flow of transferred heat is almost the same, the temperature at the tip is much lower than it is at the tip of the cylindrical pin. Temperature of the cylindrical pin can be approximately calculated from the formula below (while disregarding radius at the curves and radial temperature drop): _

(_

( ) Tz-T:p+~

) cosh [ m(z-L-0.004)J

T:p

coshmL

(1)

,

where T, is an average temperature at the peg base determined by means of FEM. This temperature measures approximately T, ~ 118.469°C. Parameter m formulated as

m=J4asp Ad '

(2)

where d is the peg's diameter, measures m==

4·80 48 ·0.006

==33.33(3)l/m.

Therefore, the tip temperature of the cylindrical pin is

T(L + 0.004) = Tw max ,

=

= 400+ (118.469 -400)

1 ) cosh 33.3333·0.0225 (

182.548°C.

As one can see, this temperature is close to the temperature Tw,max = 186.65°C obtained by means of FEM. Heat flow at the pin base can be calculated from formula

2 2 Q=_ Jrd A aT =-A Jrd m(I;, _I;p)tghmL=_48JrO.~062 4 8z z=0.004 4

x

(3)

x 33.3333(118.469 - 400 )tgh(33.3333. 0.0225) == 8.0893 W.

The obtained value approximates the value determined by means of FEM, = 8.892 W. However, from the calculations carried which is equal to

o..

out with the use of FEM, it is clear that pin-base-temperature is higher than the pin-free wall temperature from the combustion-gases-side, i.e. wall temperature for z = 0.004 m at a significant distance from the pin axis for,

Literature

307

e.g. r > 2d. Due to the application of FEM, one can use the actual dimensions of the pins shape in the calculation, e.g. the curved edges or the twodimensional character of the temperature field in the pin and the wall, to which the pin is attached.

Literature 1. Anderson JD (1995) Computational Fluid Dynamics. The Basics with Applications. McGraw-Hill, New York 2. Clough RW (1980) The finite element method after twenty-five years: a personal view. Computers & Structures 12, No.4: 361-370 3. Courant R (1943) Variational methods for the solution of problems of equilibrium and vibrations. Bull. of the American Mathematical Society 49: 1-23 4. Eisenberg MA, Lawrence EM (1973) On finite element integration in natural coordinates. International J. for Numerical Methods in Engineering 7: 574575 5. Fletcher CAJ (1984) Computational Galerkin Methods. Springer, New York 6. Huebner KH (1975) The Finite Element Method for Engineers. Wiley, New York 7. Turner MJ, Clough RW, Martin HC, Topp LJ (1956) Stiffness and deflection analysis of complex structures. J. of the Aeronautical Sciences 2, No.9: 805823

12 Finite Element Balance Method and Boundary Element Method

In this chapter, the finite element balance method (FEBM) and boundary element method (BEM) are discussed in depth. Also examples are given to demonstrate how two-dimensional steady-state temperature distributions can be determined using FEBM and BEM. The obtained results are compared with the results from FEM calculations, which were carried out by means of the ANSYS program with a highly dense finite element mesh.

Exercise 12.1 Finite Element Balance Method Describe finite element balance method.

Solution Transient heat conduction phenomenon can be described by the following equation

C(T)P(T)~~ =-\7·4, where

it

(1)

is a heat flux vector formulated by Fourier Law

it = -A(T)VT.

(2)

Thermo-physical properties such as specific heat c, thermal conductivity

A and density p are known temperature functions. Numerical solution will be carried out using finite element balance method. Balance methods, based on finite elements, allow solving heat conduction problems in complex shape bodies. They increasingly become ever more popular. Lets consider finite volume V with a boundary surface S. Heat balance equation, which allows for the variability of thermo-physical properties and which is integrated within volume ~ has the form

310


fC(T)p(T) aT dV = -

at

v

fV' 'qdV .

(3)

v

By applying mean value theorem to the left-hand-side of (3), while theorem of divergence to the right-hand-side, one obtains

Vc(f)p(f) dT =- fq ·ndS , dt

(4)

s

where the upper dash stands for the appropriate mean value in the finite volumeV.

For the purpose of simplification, finite element equations will be presented in two dimensions and in Cartesian coordinates. Equation (1) assumes the following form:

C(T)p(T) aT =~[A(T) aT] +~[A(T) aT].

at ax

ax

ay

By

(5)

An arbitrarily selected region, in which the heat flow is analyzed, was divided into triangular tri-nodal elements, marked by continuous lines (Fig. 12.1). Next, the center point of a triangle was connected with the center points of sides. This is the way in which continuous lines define the boundary of the entire region and of the individual elements, while broken lines define the control volumes. Striped regions are the examples of three control volumes. One of them is assigned to an internal node, while two to boundary nodes. In this discretisation, broken lines approximate boundary curves. Two-dimensional mesh in finite volumes can be also created by means of the Voronoi polynomials. This is when the broken lines that define convex control volumes intersect continuous lines, which define the elements, at right angles. One triangular element was evaluated; it is shown in Fig.12.2. Integral equation similar to (5) can be written when the energy preservation principle for finite volume V1aoc is applied. Equation (4) can be written in the following form

[ a}q.ndS+ fq·ndS]=-~aocC(~)p(~)d~, ~

(6)

0

where n is a normal unit vector directed to the outside of the element surface ds, while q is heat flux

q = -"l(T)VT.

Exercise 12.1 Finite Element Balance Method

311

i=')

i=l

Fig. 12.1. Irregular region divided into triangular elements and finite volumes

Fig. 12.2. Typical tri-nodal element with an assumed local coordinate system

To solve (6), one is required to define the functions that interpolate temperature T, thermal conductivity A, density p and specific heat c. Linear function was selected for temperature interpolation within the triangular element. Each element node has one degree of freedom, i.e. unknown temperature T", Temperature at an arbitrary point with x, y coordinates inside the element is formulated as follows: (7) Assuming that

(8)

one obtains

I;.e == a l + a2 • Xl + a 3 • YI,

r;e == a

l

+ a2 • x3 + a3 • Y3 •

(9)

Once (9) are solved with respect to at' a 2 and a 3 , one obtains

al

= 2~[(X2Y3 -X3Y2)~e +(X3YI-X1Y3)T2e + (X1Y2 -X2Yl)J;e],

a2 = 2~[(Y2 -

Y3)~e +(Y3 - Yl)T; +(Yl - Y2)J;e],

(10)

312


(10)

where Yl

Y2 = elementsurface. Y3 It is necessary to determine heat flux q in order to solve (6). We can determine qin every element by summing up the components in x and y direction (11)

where i, j are versors in x and y direction. Interpolation function, present in (6) and used for the approximation of variable q, has the form

4 = [ -A( T") 2~ ((Y2 - Y3 )I;e + (Y3 - Yl vt; + (Yl - Y2 )T;e)} + (12)

+[-A(Te)2~((X3 -x2)I;e +(xl -x

3)1;e

+(x2-xl)T;e)}.

Normal vectors Doc and D oa' which are needed for the calculation of integrals in (6), are given by

On the basis of (12) and the local system of coordinates x, y showed in Fig. 12.2, the integrals that appear in (6) can be written in the form

fq·uds a

=[

qx' q l y

[-Ya' a] ~ X

14' tids =[qx,qy } [Yc,-xcl ~

1 2

Xa

2

+ Ya 1

2

2

+ Yc By substituting (12) into (13), one obtains o

Xc

~X~ + Y~ , ~X; + Y; ·

(13)

Exercise 12.1 Finite Element Balance Method

313

}q·nds = i(TJ[((Y2 - Y3)~e +(Y3 - Yl)J;e +(Yl - Y2)~e)l Ya2A a

- i(T,,) [((X3-X2)~e +(Xl -x3)T2e+(X2-Xl)~e)lXa' 2A

_

}q. nds = A2A (1;,) [((Y2 - Y3 )~e + (Y3 - Yl )T; + (Yl - Y2 )~e) l Yc-

(14)

o

- i;~)[((X3 -X2)~e + (Xl -X3)J;e +(X2-Xl)~e)lxc, where

Xl

+X

2 =--

X

2

a

Xl

Xc

=-

+X3 2

Ya

= YI + Y2.

2'

'

Element 1-2-3 contributes to the energy balance equation written for the entire finite volume, which surrounds node 1 when (14) is substituted into (6) (Fig. 12.2).

Fig. 12.3. Finite volume that surrounds internal node n

In order to write the energy balance equation for the entire finite volume, which surrounds node n (Fig. 12.3), one should sum up the contributions made by all the elements, which contain node n. The energy balance equation for finite volume around node n is written in agreement with the standardized notations shown in Fig. 12.3.

314


t8~i [(1; -J:){[1(J:)+1(T; ~J: )][(Yi+1 - Yn)(Yi + Yn)-(Xn-Xi+1)(Xi +xn)J-[1(Tn)+1(T;+I;J: )][(Yi+1 - Yn)(Yi+1 + Yn)-(Xn-Xi+1)(Xi+1+Xn) ]}+(T;+1 -J:){[1(J:)+1(T; ~J:

)]x

(15)

1(

x[(Yn - Yi)(Yi +Yn) - (Xi - Xn)( Xi + Xn)] - [1(J:) + T;+I; J: )] x X[ (Yn - Yi)(Yi+1 + Yn) - (Xi - Xn)( Xi+1+ Xn)] }] = =-c(J:)p(J:)

dT 1 M

d; 3~Ai'

where

1 [1

n

A. =-2 det 1 xx. 1

1

1

X i +1

y.

.. 1

.

Yi+l

If we write heat balance equations for all finite volumes (Fig. 12.1), we obtain the system of N non-linear ordinary differential equations, whose solution are the temperatures in nodes assigned to the corresponding finite volumes. The number of equations equals the number N of finite volumes. Initial condition determines initial temperature values in all nodes. In a case when a direct problem is to be solved, the ordinary differential equation system can be solved, among others, by Runge-Kutta method. Finite elements balance method can be also applied when solving inverse problems [4,8].

Exercise 12.2 Boundary Element Method Describe how boundary element method is applied when solving steadystate heat conduction problems.

Solution In contrast to classical finite element method (FEM) , the analyzed region is not divided into finite elements when using boundary element method

Exercise 12.2 Boundary Element Method

315

(BEM)-only its boundaries [2, 3, 5, 6]. This is possible due to the transformation of the analyzed differential heat conduction equation into the equivalent integral boundary equation. BEM is especially useful for solving partial elliptical equations, which describe steady-state heat conduction, fluid flow and potential distribution in an electrostatic field. In order to solve the boundary problem, the boundaries of the region are divided into elements, as it is done in FEM. Next, the integrals, which results from the division, are approximately calculated. The number of elements in BEM is, therefore, much lower than it is in FEM. The drawback of BEM is that it is necessary to determine the so-called fundamental solution and that is something that one is able to do for only a limited number of phenomena. BEM will be discussed in greater detail using the example given below, in which we determine two-dimensional steady-state Laplace equation (1)

where u(x, y) == T(x, y) is temperature in region R shown in Fig. 12.4. tuls

YL: Fig. 12.4. Division of a boundary into finite elements in a two-dimensional region

Temperature uses) is assigned on one part of the boundary designated as su' while heat flux iJs(s) is assigned on part Sq (2) (3)

where

q(s)=iJ(S)/A.

316


A new function veX, y) is introduced in the boundary element method; it is continuous and differentiable in the region R confined by curve s. On the basis of the divergence theorem applied to vector field uVv, one has

4uVv.ds=fV.(uVv)dxdy= f [uV 2v+(Vu).(Vv)] dxdy. R

(4)

R

From the same theorem of divergence applied to vVu, one has

4 vVu ·ds = fV ·(vVu )dxdy = f [vV 2u R

+(Vv). (Vu)] dxdy.

(5)

R

By subtracting sides (5) from (4), one obtains

f(uV 2V-VV 2U )dxdy = f(uVv-vVu ).ds.

(6)

R

Equation (4) is usually defined as the Second Green Theorem. Furthermore, taking into account the following relations

Vv ds

==

\Iv· nds

==

-ds

av an

(7)

au an

(8)

and

\lu -ds = \lu -tids =-ds Equation (6) can be transformed into a form

(9) Equation (9) is used in BEM. In order to eliminate the surface integral in (9), one assumes that function v(x, y) satisfies Laplace equation in an infinite three-dimensional space Roo or in an infinite two-dimensional plane. A unit source is assumed at (Xi, Yi) coordinate point. Function v(x, y) should satisfy, therefore, equation (10)

where J is the Dirac function, which has the following properties

s = 0, Ji

~oo,

gdy

X=f:.Xi

gdy

X=Xi 1

fJidxdy = 1. R

i Y =f:. Yi'

Y = YP

(11)


317

In BEM function v (x, y) is called the fundamental solution. It can be determined in the similar way temperature field around a linear or point heat source (Chap. 25). Laplace equation V v= 0 has the form

_1 ~(rm dV]==o, r" dr dr

(12)

where m = 1 for the two-dimensional problem and m = 2 for the threedimensional problem. Symbol r is the distance of a given point from a heat source:

r=~(x-xY+(y-yY . Solution of (12) has the form 1

v == Cln- + C1 r

c

v == - + C1 r

dla

dla

m == 1,

(13)

(14)

m == 2 . m

Once (12) is integrated twice (after it is multiplied by r ) , the solutions (13) and (14) are obtained. For the fundamental solution, one assumes that C1 = O. Constant C is determined on the basis of the third property of the Dirac function noted in (11). By applying the divergence theorem to (10), one has

JV 2vdV == Rs

-

J8(x-xi ' Y -

Yi )dV == - 1,

Rs

m==l

r

linear heat source (xi,YD Fig. 12.5. Linear heat source in an infinite space (m = 1)

(15)

318


where R B is the region around the heat source. The outer surface of this region is SB. Constant C will be determined for the two-dimensional problem (Fig. 12.5), in which the integration region is a cylinder with radius 8 and height L = 1 m. Once the theorem of divergence is applied to the first integral in (15), one obtains

fV2VdV= f(Vv).ndS= fav dS= s,

Re

s,

an

avl ar

s..

(16)

rv e


Se

avl ar

=-1 ,

(17)

r=c

where

S; = 2:r8.

(18)

Once derivative of function (13) is calculated

av ar

C 1

rv e

from (17), one obtains

hence C=_l. 2:r

(19)

Therefore, the fundamental solution for the two-dimensional problem has the form 1 1 (20) v=-ln2:r r' where r=~(x-xJ2+(y_yY. From the standpoint of physics, one can use the concept of heat exchange by conduction to explain in a straight-forward way how constant C is determined from Gauss-Ostrogradski theorem (16). Linear heat source with a power Q/L = 1W/m is located at the point (Xi' y); therefore, power Q = 1 W is generated within the length of L = 1 m. Heat source power per unit of volume is


.

Q

(21)

qV=~L' Jr

where

4v

319

r.

3

is expressed in W/m • If the outer radius r of a cylindrical heat

source becomes smaller, then

4v

becomes larger, i.e. (22)

Power Q generated by the heat source outflows to the surrounding space. Function vCr) that shows in such case temperature distribution within the area whose heat conduction coefficient equals A == 1 W/(m·K), should satisfy the heat balance equation. Source-generated heat flow must be passing through a lateral surface of the cylinder (Fig. 12.5)

.

avl

Q=-2Jr8LA-..

'

ar r=&

(23)

hence, one gets

Q= -2Jl"&A 8v Once we substitute

8v/ arlr=& = -C / 8

, Z

I

.

(24)

ar r=&

L

Q/L

== 1 W/m, A == 1 W/(m·K) and account for

(23), we have (19). On the basis of divergence theo-

rem (15), one can also determine constant C in (14) for the spatial problem. Constants C and C1 in (14) are C == 1/4n, C1 == o. If the fundamental solution (20) is known, one can calculate v and avian, which appears on the right-hand-side of (9). By substituting (1) and (10) into (9), one has for (Xi, Yi) E R and (Xi, Yi) ~ s

f(uV 2v - vV 2u ) dxdy R

= - fuo; dxdy = -u; .

(25)

R


-u = r(u an8v -v aU)dS. an i

(26)

s

On the basis of (26), one can calculate temperature ". at any point (Xi' y) within region R, if temperature U and the derivative in normal direction avian are known for the whole boundary s. According to boundary conditions (2) and (3), temperature and normal derivative are not known for the whole boundary, but only for the part of that boundary. Equation (26), therefore, can be used to calculate temperature u i once temperature U on the boundary section Sq and normal derivative aulan on the boundary

320


section su are determined. This is why it is necessary to find relation between known and unknown temperatures and heat fluxes on boundary s. Such dependency is obtained under the assumption that point (Xi' y) lies on the boundary s. Equation (9) assumes then the following form [1-3]

c.u. 11

au aVJ ds = f (v--ua a ' n

s

(27)

n

where r.is the constant dependent on the boundary shape at point (Xi' y). If the boundary is smooth at this point, then ci = 1/2. Once the following notations are introduced

_ au = an'

(28)

u * =V,

(29)

q

_*

q

av

(30)

= an'

Equation (27) can be written in the form CiU i

J

J

+ u({ds = u*qds.

(31)

Next, discretisation of the integral (31) is carried out. The boundary of the analyzed region is divided into N elements (Fig. 12.6). Function u and its derivative au/an are assigned on every element by means of simple functions. In the most straightforward case, values u and au/an are assigned to the center points of elements called nodes. Boundary of region s is approximated by means of a piecewise linear function. The node lies in the center of the section. At this point the boundary is smooth; therefore, ci in (31) is ci = 1/2, i = 1, ..., N. ~u = const en

u> canst

Fig. 12.6. Boundary division into finite elements; values u and au/an are constant within the.length of the element


321

The discrete form of (31) is N

N

-». + L Juq*ds = L Ju*qds, j=l ~

i = 1, ...,N,

(32)

j=l ~

where s. is the length ofj-element. Functions u and }

q = au/an are constant

within the length of the element; thus, once the following notations are introduced (33) (34) equation system (32) for points i, which lie on the region's boundary, can be written in the form (35) Integrals (33) and (34) are usually numerically calculated using, for instance, Gauss quadratures. (36)

Gij

S. K * =--l.... LUkWk,

2

(37)

k=l

where sjis the length ofj-element, and wkthe weight coefficient, which corresponds to k-point during numerical integration. Once the notations below are introduced

= IJ

H ..

iI.. , IJ

{ Hi) +1/2, "

(38)

equation system (35) can be written in.the form (39) System (39) can also be written in the matrix form

Hu =Gij,

(40)

where Hand G are the coefficient matrices, whose dimensions are N x N, while u and q are column vectors with N dimensions. The equation system,

322


however, only contains N = Nu + Nq unknowns, since Nu values of temperature u are assigned on the section of boundary su' while Nq values of heat flux 4s are known on the boundary Sq (more specifically, Nq values where au/an = 4s/A). Therefore, there are Nu heat flux unknowns on the boundary section sand Nq temperatures on the boundary sq. In total, N unknowns are u to be found. One can transform the equation system (40) by moving the mathematical terms, which contain the unknowns, to the left-hand-side of the equation. The system is reduced to a form (41)

Ay=b,

where A is the matrix of coefficients, whose dimensions are N x N, y is a column vector of N dimension that contains N q of temperatures u and N u derivatives au/an. Once the equation system (41) is solved, one can determine values u and au/an at the boundary of the analyzed region. Therefore, values u and au/an are known on the boundary s. Furthermore, values v and avIan can be calculated in all N nodes. Temperature at inner points (Fig. 12.7) can be calculated by means of (26), which has the following discrete form: (42)

Boundary element method is also a very effective tool for solving transient problems. Its main advantage is that in comparison to FEM, it uses a significantly smaller number of elements, since only the boundary is discretisized. Its disadvantage is that it is necessary to determine fundamental solution, which in the case of convective heat transfer problems is difficult to find.

s

Fig. 12.7. Diagram that shows the calculation of temperature u at point i, which

lies inside the region

Exercise 12.3 Determining Temperature Distribution in a Square Region

323

Exercise 12.3 Determining Temperature Distribution in Square Region by Means of FEM Balance Method Determine steady-state temperature distribution in a square region, whose side is a = 2 em in length. Assume thermal conductivity coefficient of the medium to be at A = 42 W/(m·K). Boundary conditions are illustrated in 2 Fig. 12.8. Use the following data for the calculation: qB = 200000 W/m , a = 60 W/(m

2·K),

r, =20°C, t, = 100°C. y

4

a

x

2 a Tcz·

Fig. 12.8. Diagram of the analyzed region; it illustrates boundary conditions and the division of the region into finite elements

Solution Node coordinates are as follow: 0.00 m, YI == 0.00 m; X 2 == 0.02 m, Y2 == 0.00 m;

Xl ==

x3 == 0.02 m,

Y3

== 0.02 m;

x4

== 0.00 m,

Y4

== 0.02 m;

Xs

== 0.01 m, Ys == 0.01 m.

One can write heat balance equation for the finite volume, which surounds node 5 using (15) from Ex. 12.1 and by substituting n = 5; i = 1,2,3,4

324


--1_[(1; - Ts){ 2A[(Y2 - Ys )(YI + YS) - (XS- X2)(X1 + XS)]g·AI

-2A[(Y2 - YS)(Y2 + YS)-(XS-X2)(X2+XS)]}X x

(1; -Ts){2A[(Ys - YI)(YI + YS)-(X I-XS)(XI+XS)]-

-2A[(Ys - YI)(Y2 + YS)-(X I-XS)(X2+Xs)]}J--1-[(1; -Ts){2A[(Y3 - YS)(Y2 + Ys)-(xs -X3)(X2+XS)]g·A 2

-2A[(Y3 - YS)(Y3 + Ys)-(xs-X3)(X3+xs)]}x x

(1; - Ts){ 2A[(Ys - Y2 )(Y2 + Ys) - (x2- xs)( x2+ xs)]-

-2A[(Ys - Y2)(Y3 + ys)-(x 2-XS)(x3+Xs)]}J1 [

- - (1; -Ts){2A[(Y4 - YS)(Y3 + Ys)-(xs-X4)(X3+xs)]g·A 3

-2A[(Y4 - YS)(Y4 + Ys)-(xs -X4)(X4+xs)]}x x(~ -Ts){2A[(Ys - Y3)(Y3 + ys)-(x3-XS)(x3+XS)]-

-2A[(Ys - Y3)(Y4 + ys)-(x3-XS)(x4+XS)]}]__1_[(~ -Ts){2A[(YI - YS)(Y4 + Ys)-(xs -XI)(X4+XS)]8·A4

-2A[(YI - YS)(YI + Ys)-(xs -XI)(XI+xs)]}x

x(1; -Ts){2A[(Ys - Y4)(Y4 + ys)-(x4-XS)(x4+XS)]-2A[(Ys - Y4 )(YI + Ys) - (x4- xs)( XI + xs)]} ] = 0,

(1)


325

By substituting the numerical values into (1), the following equation for node 5 is obtained:

42·2 [{(~ -Ts)(0-0,0002)+(1; -Ts)(0,0002-0,0004)} +

8·0,0001

+{(1; -Ts)(0,0004-0,0006)+(1; -Ts)(-0,0002-0)}+ +{(1; - Ts)(0- 0,0002) +(~ - Ts)(-0,0006 - (-0,0004))} + +{ (~ - 7;)(-0,0004- (-0,0002)) +(1; - Ts)(-0,0002 - O)}] =0, -[{(~ -7;)(-2)+(1; -Ts)(-2)}+{(1; -7;)(-2)+(1; -Ts)(-2)} +

+{(1; -7;)(-2)+(~ -7;)(-2)}+{(~ -7;)(-2)+(~ -7;)(-2)}]=0. By substituting T2 = 100°C and T3 = 100°C, one obtains ~ +~ -4·~

=-200.

(2)

Heat balance equation for the finite volume, which surrounds node 4 can be written in the following form (n = 4; i = I, 5, 3):

__I_[(~ -~){21[(ys - Y4)(YI + Y4)-(X4-XS)(xl +x4)J8·A4

-21[(ys - Y4)(YS + Y4)-(X4-xs)(xs+x4)J}x x(7; -~){21[(Y4 - Yl)(YI + Y4)-(X} -X4)(X1 +x4)J-21[(Y4 - Yl)(YS + Y4)-(X1 -x4)(XS+x4 )J}J--1-[(7; -~){21[(Y3 - h)(Ys + Y4)-(X4-x3)(XS+x4)J8·A3

-21 [(Y3

- Y4)(Y3 + Y4)-(X4-X3)(X3+x4)]}x

x(1; -~){21[(Y4 - Ys)(Ys + Y4)-(XS-x4)(XS+X4)]-21[(Y4 - YS)(Y3 + Y4)-(XS-X4)(X3+X4)J}J+qB~=0, where from, after substitution of the numerical values, one has

(3)

326

12Finite Element Balance Method and Boundary Element Method

42·2 8·0.0001

[{(1; -~)(-0.0002-(-0.0002))+(Ts -~)x

x( 0.0004 -

0.0006)} + {(Ts

x( 0.0002 -

0.0002)} ] + 200000. 0.~2 = 0,

- T4 ) ( 0.0002 -

0.0004) + (1;

- ~) x

42[{ (1; -~)(O)+(Ts -Tt)(-2)}+ -4 +{(Ts -Tt)(-2)+(1; -Tt)·0}]+2000=0, (4)

1; -T4 =- 47.6.

Heat balance equation for the finite volume, which surrounds node 1 can be written in the following form (n = 1; i = 2,5,4):

__l_[(J; -1;){2A[(Ys - Yl)(Y2 + Yl)-(X1-XS)(x2+X1)]8·AI

-2A[(Ys - Yl)(YS + Yl)-(X1-xs)(xs+x1)]}x x(Ts -1;){2A[(YI - Y2)(Y2 + Yl)-(X2-X1)(X2+X1)]-

(5)

-2A[(YI - Y2)(YS + Yl)-(X2-x1)(XS+x1)]}J-

__I_[(Ts -1;){2A[(Y4 - Yl)(YS + Yl)-(X1-x4)(XS+x1)J8·A4

-2A[(Y4 - Yl)(Y4 + Yl)-(X1-X4)(X4+x1)]}x x(Tt -1;){2A[(YI - Ys)(Ys + Yl)-(XS-x1)(XS+x1)J-2A[(YI - YS)(Y4 + Yl)-(XS-X1)(X4+Xl)]}J+qB~+Qa =0, al2

Qa = Ja(Tcz -T(x,O))dx= o

=a{(Tcz - 2~[(X2Y3 -X3Y2)1; +(X3Yl-X1Y3)J; + (X1Y2 -X2Yl)Ts])~2

1

-2A[(Y2-Y3)1; +(Y3-Yl)J; =a

a } +(Yl-Y2)Ts]-g

=

{(Tcz - 2a~/4[a~1; ])~- 2a~/4[(-~)1; +(~)J; ]a:}.


327

After substitution of the numerical values, one has

-1: J~]=60'20'0.02 -60. 3.0.02.r,_ Q.a =a[(Tcz -1:1 )~-[T 2 2 1 8 2 8 1 -60· 0.02'1;

8

=12-0.45·~ -0.15,1;,

42·2 [{(1; 8·0.0001

-~)(0.0002-0.0002)+(Ts-~)x

x( -0.0004 - (-0.0002))} + {(Ts - ~)( 0.0002 - 0.0004) + +(~ -~)(-0.0002-(-0.0002))}J+200000' 0.~2 + +(12-0.45·~ -0.15.1;)=0,

42 -4[ 2(Ts - ~)( -2)] + 2000+ (12 - 0.45· ~ - 0.15· 1;) = 0, -

42.45·~ +42·~

=-1997.

(6)

The solution for equation systems (2), (4) and (6) is

T, = 194.145°C;

~

= 146.545°C.

Calculations by means of the ANSYS program were also carried out and the following results were obtained: ~

= 146.545°C.

Exercise 12.4 Determining Temperature Distribution in a Square Region using Boundary Element Method Determine temperature distribution in a two-dimensional region, which measures 6 x 6 m (Fig. 12.9). The thermal conductivity of the material is A, = 50 W/(m·K). Boundary conditions are presented in Fig. 12.9. Temperatures are assigned on lateral surfaces, while heat flux on an upper and

328


lower surface. Determine temperature distribution by means of BETIS program [1]. Compare the obtained results with the values determined by means of FEM.

Solution Temperature distribution within a two-dimensional region shown in Fig. 12.9 is governed by the heat conduction equation

a2T a2T -+-=0 ax2

(1)

By2

and by boundary conditions Osys6 m,

(2)

Osys6 m,

(3)

= 10000 W/m 2 ,

-A aT By

Osxs6 m,

(4)

0~x~6

(5)

y=o

=0 W/m 2 ,

-A aT

ay

m.

y=6m

Boundary conditions (4) and (5) will be transformed into a form

et By

= _10000 = -200 KIm A

y=o

aT By

=0. y=6m

(6)

'

(7)


2

3

329

4

__- - + - -....- - - - - t l - - -__- - + - -..'--.-- ..

(0,0) I'

q =10000

W/m

(6,0) x

2

Fig. 12.9. A diagram that illustrates boundary conditions and boundary division into finite elements in BEM

Table 12.1. Node temperature values (Fig. 12.10) calculated by means of BEM andFEM Temperature rOC] Node no. 1 2 3 4 5 6 7 8 9

Temperature rOC] Node no.

BEM

FEM

300.00 607.38 507.38 0.00 0.00 0.00 0.00 134.17 234.17

300.00 612.91 512.91 0.00 0.00 0.00 0.00 136.37 236.37

10 11 12 II 12 13 14 15

BEM

FEM

300.00 300.00 300.00 336.71 252.98 246.05 236.71 152.98

300.00 300.00 300.00 350.09 258.24 255.04 250.09 158.24

330


ANSYS 5.5.3 DEC 19 2001 17: 35: 50 NODAL SOLUTION STEP=l SUB

=1

TIME=l

TEMP

(AVG)

RSYS=O

PowerGraphics EFACET=l AVRES=Mat SMX

..

.. •

00II IIiI

I II D

• ..

=615.471

o 68.386 136.771 205.157 273.543

~~~:~~~

478.699 547.085 615.471

Fig. 12.10. Temperature distribution in an analyzed region determined by means ofFEM

Temperature distribution will be determined by means of BEM using BETIS program [1]. Conditions (2)-(3) and (6)-(7) will be used for the calculation. The boundary of region was divided into 12 boundary elements (Fig. 12.9). Temperature was calculated in 12 nodes, which lie on the boundary and at internal points 11-15. Linear functions were utilized for temperature approximation within the length of the element. Temperature distribution was also determined by means of FEM with ANSYS program (Fig. 12.10). Analyzed region was divided into 900 elements (mesh 30 x 30). Table 12.1 shows calculation results obtained by means of BEM and FEM. The results on the region's boundary show good agreement; however, the level of agreement is lower for the internal points 11-15. One should note, nevertheless, that obtained results show good accuracy, in spite of the fact that the boundary in BEM was divided into a small number of elements.

Literature

331

Literature 1. ANSYS (2000) User's Manuals. Swanson Analysis Systems, Inc. 2. Brebbia CA, Dominguez J (1992) Boundary Elements: An Introductory Course. Computational Mechanics, Southampton 3. Brebbia CA, Telles JCF, Wrobel LC (1984) Boundary Element Techniques. Theory and Applications in Engineering. Springer, Berlin 4. Duda P, Taler J (2000) Numerical method for the solution of non-linear twodimensional inverse heat conduction problem using unstructured meshes. International Journal for Numerical Methods in Engineering 48: 881-899 5. Evans G, Blackledge J, Yardley P (2000) Numerical Methods for Partial Differential Equations. Springer, London 6. Paris F, Canas J (1997) Boundary Element Method, Fundamentals and Applications. Oxford University Press, Oxford 7. Riley KF, Hobson MP, Bence SJ (1998) Mathematical Methods for Physics and Engineering. Cambridge University Press, Cambridge 8. Taler J, Duda P (1999) A space marching method for multidimensional transient inverse heat conduction problems. Heat and Mass Transfer 34: 349-356

13 Transient Heat Exchange between a Body with Lumped Thermal Capacity and Its Surroundings

In this chapter, we will analyze the process of heat exchange under the assumption that thermal capacity of a solid is concentrated in one point. Such assumption can be made for number of cases in practice, since the thermal conductivity of a solid is very large or the outer surface heat transfer coefficient is very small. Solutions for step-change in the medium temperature are presented here as well as the solutions that can be used in instances when the medium's temperature changes periodically or is a linear function of time. Furthermore, an inverse problem is being solved; it is based on the premise that one has to find the medium's temperature on the basis of known thermometer temperature history in time. Derived formulas are applied to the calculation of dynamic temperature measurement errors for a step-change and linear-change temperature of a medium. Simple and inverse problem is illustrated on the basis of a given example: the history of temperature of an industrial thermometer used for measuring periodically variable temperature of a superheated vapour.

Exercise 13.1 Heat Exchange between a Body with Lumped Thermal Capacity and Its Surroundings Derive a differential equation to describe convection heat exchange by way of between a body with concentrated mass and its surroundings. Thermal diffusivity coefficient a is constant and time-invariant. Solve the obtained equation when the temperature of a medium undergoes a step-change.

Solution If the thermal conductivity A of a solid is extremely large or heat transfer coefficient a on the body surface is extremely small, then the temperature within the whole body volume is almost the same, i.e. temperature differences inside the body are insignificant. The following condition can be assumed for irregular-shape-bodies:

334

13 Transient Heat Exchange between a Body with Lumped Thermal. ..

Bt =

a(f)

sO.05

A

(1)

If the above condition is met, one can neglected the temperature drop inside the body. In (1) B( is the Biot number, V a body volume, while As an outer surface area of the body. Quotient L* = VIAs is a characteristic body dimension. A characteristic dimension of a sphere with radius R is

L* _ V - As

_ 4 ;rR

3 _

R

-3 4JrR -3 2

(2)

Once we substitute (2) into (1), the condition under which we assume that the heat conduction model with lumped mass has the following form for a sphere:

aR

-50.15. A

(3)

Heat balance equation will be written for an arbitrary shape body. Body volume is V, while Asis the outer surface of the body (Fig. 13.1). Thermal conductivity A, density p and specific heat c are constant and temperature invariant. Assuming that initial body temperature is

rlt=o = t;

(4)

and that temperature of the medium Tcz(t) > To' i.e. the body is heated, the energy balance has the form (5)

where u

= cvTis a unitary internal temperature, while m =pVa body mass.

Fig. 13.1. A body with concentrated (lumped) thermal capacity

Exercise 13.1 Heat Exchange between Body with Lumped Thermal Capacity

335

Because specific heat is practically the same for a solid when pressure and volume is constant, i.e. cp = c, = c, the energy balance (5) assumes the form

dT(/)

cpv--+ aAsT(/) = aAs~z (I). dl

(6)

Once time constant is introduced

cpv

r=-a A' s

(7)

Equation (6) can be transformed into a form (8)

It is a heterogeneous differential equation of the first order. If temperature of the medium undergoes a step-change (Fig. 13.2), one can easily determine the solution for (6), if it is assumed that (9) T Tcz 1 - - - - - - - -

o Fig. 13.2. Temperature step-change in a medium

Equation (8) and initial condition (4) have the form then

dB

r-+B=O, dl

(10) (11)

After separation of variables in (10)

dB 1 -=--dl

B

r

(12)

336

13 Transient Heat Exchange between a Body with Lumped Thermal...

one obtains In B = -t/ t + C or (13) Once we account for boundary condition (11), we can determine constant C1: C1=Bo• Solution (13) assumes the form then

B(t)=Boe- t /

T ,

(14)

where time constant r is given by (7). Heat flow delivered to the body at time t iso

Q(t)=aAs[Tcz -T(t)J.

(15)

The quantity of body-transferred heat in time from 0 to tis t

Q(t) = fQ(t )dt = aAs(Tcz - To )r(1- e-t1r ) .

(16)

o

Exercise 13.2 Heat Exchange between a Body with Lumped Thermal Capacity and Surroundings with Time-Dependent Temperature Write general formula for temperature of a body with concentrated mass (small thermal resistance), if temperature of a medium Tczchanges in time. Derive a formula for body temperature, if the medium's temperature Tcz(t) =a + bt changes at constant rate, equal to b, where a is a constant.

Solution Differential equation, which describes body temperature changes, has the form (Ex. 13.1, (6))

cpV ~ +a(t)AJ(t) = a(t)AJcz (t)

(1)

when initial condition is (2)

Once (1) is divided by

cpV~

one obtains

dT + p(t)T=q(t), dt

(3)

Exercise 13.2 Heat Exchange between a Body...

337

where p ( t ) = a (t ) As ,

cpV

a(t)A q(t) = cpV

S

(4)

J:z (t).

It is a heterogeneous differential equation of the first order. First we will determine the solution for homogeneous equation. In (3) we assume that q(t) = 0, following that we obtain, using variable separation method T

- Jp(t)dt

= Cle

,where C1

• IS

a constant.

(5)

According to the variation of constant method, solution (5) is written in the form (6)

Once (6) is substituted into (3) and mathematical operation carried out, one obtains

' - Jp(t)dt CIe

_

C1() () - Jp(t)dt + p ( t) I Ct ( ) e- Jp(t)dt -- q () t pte t ,

(7)

where

' ( ) - () Jp(t)dt , CIt-qte

(8)

C,=dCI 1 dt· Once (8) is integrated, one has

f ()

- q t e Jp(t)dt +C, CI( t) -

(9)

where C is a constant. By substituting (9) into (6), we has Jp(t)dt t e dt. T()t = Ce- fp(t)dt +e- Jp(t)dt Jq ()

(10)

Constant C is determined from the initial condition (2). If the medium's temperature changes according to formula (11)

338

13 Transient Heat Exchange between a Body with Lumped Thermal...

where a and b are constants and coefficient a is constant too, then from (4) we have

p(t)= aAs cpV

=!,

q(t)= aAs(a+bt)

= a+bt.

cpV

t

(12)

t

By substituting (12) into (10), one obtains T{t) =ce: I T + «' I T

f

a+bt

__

et IT dt.

(13)

r

Then we determine the integral below by integrating by parts

fbtellTdt = tbte'" - fb(Tilr)dT=(bTt-bT2)eIIT =bT(t-T)eIIT (14) and calculate the remaining integrals. Equation (13) then assumes the form

T(t) = Ce-

IIT

+ e-

llT br{t - r) e ae + T [

IIT

tlT ]

'

T{t)=Ce- t I T +{a+bt)-br.

(15)

From the initial condition (2), we get

To =C+a-br, hence,

C=To O. The same is done in the second case b

b

b~OCJ 0

b~OCJ 0

2'{e- C1} = lim fe-sle-Cldt=lim fe-cs+C)ldt= -e

-(s+c)b

S

OCJ

(4)

+cos +c

for s > - c. When transformF(s) is given, while functionf(t), which corresponds to the transform is the unknown, one can write the problem in the following way:

f (t) = 2' -I {F(S )} .

(5)

1

Symbol 5l- stands for the Laplace inverse transform. Selected properties of the Laplace transform are listed in Table 14.1. In the case of transient heat conduction equations, Laplace transformation is carried out with respect to time variable t. Once the solution transform is found, the inverse transformation is carried out. Table 14.1. Some of the properties of the Laplace transform

Y {clf (t) + <s (t)} = C1F ( s ) + C2G( s ) ,

y{8 nf ( x,t)} = an F(x,s) , 8x

n

8x

n

£{ff(r)dr} = F~S), dn

£ {tnf(t)} = (-1)" ds nF(s),

8f

C1

and C2 are constant

(X,t)} =sF(x,s)- f(x,O)

Y { -8-t-

2f ,t)} y { 8 8t(X 2 =s2F(x,s)-sf(x,O)- f'(x,O)

£{J(kt)}

=iFUJ

£ {ff( t )g(t- t )dr}= F(s)G( s)

It is often difficult to search for an inverse transform when one aims to find a solution in the real domain. This is why often tables are used in practice. Some of the transforms F(s) and their corresponding functions f (t), which occur when transient temperature fields are determined in a semi-infinite body, are compiled in Table 14.2.

Exercise 14.2 Formula Derivation for Temperature Distribution

355

Table 14.2. Transforms F(s) of function f (t) that occur when transient temperature fields are determined in a semi-infinite body exp(-sto) exp(-qx) exp(-qx)/q

exp(-qx)/s exp(-qx)/sq 2

erfc

~ exp(-x V-;

exp(-qx)

A

s( q+~)

~

2v at

2/4at)-xerfc

~

2v at

A

x

-erfc----G a 2~ a

In Table 14.2, the following notations were assumed:

q=~, G=exp(axA + a2~t)erfc( ~+ a~) , A 2 at A v

a

- heat transfer coefficient [W/(m 2·K)],

- thermal conductivity of semi-infinite body [W/(moK)], - spatial coordinate [m], - time [s], 2/s], a = Alcp- temperature diffusivity [m erfc x = 1- erf x, erf x - Gauss error function (appendix A). Laplace transform and its application when solving transient heat conduction problems is thoroughly discussed in papers [1, 4,7,8]. A x t

Exercise 14.2 Formula Derivation for Temperature Distribution in a Half-Space with a Step Increase in Surface Temperature Derive a formula for temperature distribution and heat flux in a semiinfinite body with a step increase in surface temperature of a half-space from an initial temperature To to temperature Ts 0

356


Solution The assumed coordinate system is presented in Fig. 14.1. T

x

Fig. 14.1. Heated half-space with a step increase in surface temperature

Temperature distribution is described by equation

er a2T -=a-2 at ax '

(1)

by boundary conditions (2)

T(oo,t) = 1'0

(3)

T(x,O) = 1'0.

(4)

and by initial condition

Once excess temperature surplus is introduced

u=T-1'o

(5)

the initial-boundary problem (1)-(4) can be expressed in the following way:

au a2u -=a-2 at ax '

(6)

u(o,t)=us '

(7)

u(oo,t)=o,

(8)


u(x,o) = O.

357

(9)

The initial-boundary problem (6)-(9) will be solved using Laplace transform. Transformation of (6) is carried out when the initial condition is given by (9); hence, we obtain 2U(x,s)

d _!... U (X,S )--0. --2dx

a

(10)

The solution of (10) has the form (11) By accounting for condition (8), from which it follows that C1 = 0, solution (11) assumes the form (12)

Once constant C2 is determined from boundary condition (7), which after Laplace transformation assumes the form

U(O,s)=~,

(13)

U(x,s)= Us e-...r;;;,·x.

(14)

s

one obtains

s

Inverse Laplace transformation is carried out using the fourth formula from Table 14.2; hence, we obtain (15)

r(x,t)-r. =erf(_x_). To -t;

2J;;{

(16)

Appendix A contains a table with function erf x. Heat flux is formulated as (17)

358


or

q(x,t) =,i(:Z: - To)

7--. e-

x

' / 4at .

'\jll

J

~=

2'\jat

kp m

(:z: - To )e- ' / 4at . X

(18)

Heat flux on the body surface is (19)

Exercise 14.3 Formula Derivation for Temperature Distribution in a Half-Space with a Step Increase in Heat Flux Derive a formula for temperature distribution in a semi-infinite body with a step increase in heat flux qs on the surface. Initial body temperature To is constant and measures.

Solution Temperature field in a half-space is defined by a differential equation

au

a at = a ax

2u

2 '

(l)

u(x,O) = 0,

(2)

by initial condition and by boundary conditions

-,i aul =.qs, ax x=o

(3)

u( oo,t) = 0,

(4)

u(x,t)=T(x,t)-ra .

(5)

where


o LL..-----

359

x

Fig. 14.2. Diagram of a half-space heated by heat flux

qs

Once the Laplace transform is applied to (1) and initial condition (2) is accounted for, one gets 2U(x,s)

d

---2-

dx

_!-U (X,S )--0. a

(6)

The solution of (6) has the form (7)

From condition (4), it follows that constant C1 in solution (7) equals zero. Constant C2 is determined from boundary condition (3), to which Laplace transform was applied (8)

By substituting (7) into (8) and accounting for the fact that C1 = 0, one obtains

c2 =~ ' ) ' where nsq

q= "Sf r;j;. a

(9)

By substituting (9) into (7), one has qx

U(x,s)= iIs eA sq

•

(10)

Once inverse Laplace transformation is carried out (Table 14.2, Ex. 14.1), an expression for temperature distribution is obtained:

360


_T

U-

7' - qs -10 --

A

[2J¥t-e

-x

2/(4at)

c. X ) . -xerlc--

2,J;;i

1[

(11)

Surface temperature of the half-space is expressed as

ul x=o =TI x=o -T = 2QsA f; ~ = 2QsJi . j;~Acp

(12)

0

Exercise 14.4 Formula Derivation for Temperature Distribution in a Half-Space with a Step Increase in Temperature of a Medium Derive a formula for temperature distribution in a semi-infinite body with a convective boundary condition.

Solution Half-space is heated or cooled by a medium with temperature Tez and an assigned heat transfer coefficient a. Half-space temperature field is defined by the heat conduction equation

au at

au ax 2

-=a2

(1) '

by initial condition

u(x,o) = 0,

(2)

and by boundary conditions (3)

u(oo,t)=o,

(4)

where u = T - To. Once Laplace transformation is carried out, solution Utx.s) has the form identical to the (12) in Ex. 14.2: (5)

Exercise 14.4 Temperature Distribution in a Half-Space

361

x

Fig. 14.3. Temperature distribution in a half-space with a convective boundary

condition

In order to determine constant C2 ' Laplace transformation will be done for boundary condition (3):

-A, aUI oX

x=o

= a(Uscz

-UI = J.

(6)

x 0

Once (5) is substituted into (6) and subsequently transformed, constant C2 is determined C2 =

a/A (1;,z - To) s ( q + a/A) .

(7)

Once (7) is substituted into (5), one has (8)

Inverse Laplace transformation is carried out using the last formula from Table 14.2 (Ex. 14.1), hence, we obtain a formula for temperature distribution

U= T - To = (1;,z - To)[ erfc 2~ - exp [ aA,x + a;~t)x

xerfc(2~+~ ~)l

(9) osxSoo.

Once the symbols are introduced

362


at

Bi= ax

FO=-2 '

(10)

A'

x

and relations accounted for

(11)

solution (9) can be written in the form ()=

T(x,t)-Ta

t: -t;

=1-erf

(I) (

2)

r;:;- -exp Bi-v Bi Fo x

2vFo

(12)

X[1-erf(21 +Bi~)}

Function (12) describes temperature distribution in the half-space with an initial temperature To, whose surface is subjected to (for time t> 0) a liquid with temperature Tcz To. The half-space can be heated or cooled by a fluid with a temperature of Tcz == const. Half-space surface temperature x == 0 is defined by the following expression obtained from (12)

*

T(O,t)=To +(~z -To)[l-erfC(~ ~

)ex

p(

a~~t)]

(13)

or

Expression (14) is also used for the experimental determination of the heat transfer coefficient a on the basis of measured surface temperature at a given time point t p ' Half-space temperature distribution in a semi-logarithmic and Cartesian coordinate system is shown in Figs. 14.4 and 14.5.

Exercise 14.4 Temperature Distribution in a Half-Space

363

LO l{x.t)-l(} 1~'Z-1(}

0.1

00

5

3

2 1

0.01

0.75

8:~

0,3 0.2

OJ (1001

0,075 0.05 0.03 0,01 0,005 1,5

-l--_--I-_ _-4-_---4-_ _4-_---lf----3r..-I

o

0,25

0.5

0.75

1.0

1.25

x

2J(ii

Fig. 14.4. Temperature distribution in a half-space with a convective heattransfer

on the surface 1.0...-----------------------. 1 Parametrprzy 1 krzvwvch "

I 1" " I !£ at = BP Fo

0.8

I }.2

I

I I I

---T-----~------T-----

1

0.6

1 1

I

I

I

I

I

I

1

I

I 1 I - T - - - - - -1- - - - - - r 1

I

I

-----

I

I I I I I I - - - - -1- - - - - - 1- - - - - 1 I

0.4

1

I

1 I

0.2

I I ~""._"__,~"'.J\.~-I- - - - - -.I- - - - - I I I I 0.5

1.0 x

15

2.0

I

2J(ii = 2jhl

Fig. 14.5. Temperature distribution in a half-space witha convective heattransfer

on the surface

364


Exercise 14.5 Formula Derivation for Temperature Distribution in a Half-Space when Surface Temperature is Time-Dependent Derive a formula for temperature distribution in a semi-infinite body when surface temperature is time-dependent.

cp(t)

Fig. 14.6. Diagram of a semi-infinite body with time-dependent surface temperature

Solution Temperature field in the half-space is expressed by a differential equation

au at

a ax

2u

-==a2

(1) '

by initial condition u

=0

for t

= 0,

x >0

(2)

and by boundary conditions u == cp(t) for x == 0, t > 0, u ==

°

for x ~

00,

t > 0,

(3)

(4)

where u = T - To' To is the constant initial temperature. Once Laplace transformation of (1) is carried out and initial condition (2) accounted for, one has 2U(x,s)

d

--2-

dx

_!... U (X,S )--0, a

(5)

where 00

u (x,s) = fe-stu (x,t )dt. o

(6)

Exercise 14.5 Surface Temperature is Time-Dependent

365

As a result of the transformation of boundary condition (3), one gets

U(x,s)=¢(s)

for

x =o.

(7)

The solution for (5) is the function (8)

Because V(oo, s) =0, constant C1in expression (8) equals zero: C1= O. Therefore, solution (8) has the form

U( x,s) = C2e-.[;7;. x .

(9)

From boundary condition (7), one obtains (10)

By accounting for (10) in (9), solution Vex, s) assumes the form U ( x, s ) = ¢(s ) e-.[;7;. x

(11)

or after multiplying and dividing by s

e-.[;7;x

U(x,s)=s¢(s) . - .

(12)

s

Taking into account that (Table 14.1) (13)

and fZ

-1

e

-.[;k.x}

-s

{

x x = erfc-=1- erf--

2~

2~'

(14)

excess temperature surplus u(x,t) can be determined on the basis of the last dependency in Table 14.1

tdrp(r)

u(x,t)= J--.erfc ~ o

Heat flux

dt

2

x

a(t-r)

dt .

(15)

q(x, t) is given by .( x,t) -__ Aau(x,t) . ax

q

(16)

366


By using a formula for derivative 2 _x2 , -d ( erfx ) =-e dx J;

(17)

heat flux (16) can be expressed in the following way:

q(X,t)=-AfdqJ(t)[-~.exp[x J. 1 o dt J; 4a(t2~ a(t2

T)

. f¥c 1 xp[ q(x,t)= - fP-t - e 1r o~

x

2

4a(t-r)

]dr, (18) T)

J·--dr. drp ( t ) dt

Heat flux on the half-space surface is

q(x,t)l_ =~Acplfdrp(r)_I_dr. x-a

1r

dt

0

~

(19)

Equation (19) is used for measuring heat flux on the basis of the halfspace measured temperature rp (t).

Exercise 14.6 Formula Derivation for a Quasi-Steady State Temperature Field in a Half-Space when Surface Temperature Changes Periodically Derive a formula for the quasi-steady state temperature field in a halfspace, when surface temperature changes periodically (Fig. 14.7). Discuss your findings.

Solution Temperature field is expressed by equation

et at

a

2r

-=a2

ax

(1) '

by initial condition O~x5/m (Fig. 14.9) when there is a periodic change in surface temperature, while t> 15/ to [3] when there is a periodically changeable heat flux. lr-~~-------....~~-------....~~

0,5

-0,5 T(O,t) -

r

~T

-1

5 10 ° Fig. 14.9. Half-space surface heat flux q., when surface temperature changes pewt

15

riodically and is described by function T(O,t) = T + ~Tsinmt - a dashed line [3]

374


For t > 5/m, one can assume that g = 0 and (35) assumes the form

lSin(

tis (t) = AllT

tot + :).

(38)

Exercise 14.7 Formula Derivation for Temperature of Two Contacting Semi-Infinite Bodies Derive a formula for temperature of two adjacent semi-infinite bodies, under the assumption that at the interface the body contact is ideal, i.e. surface temperature and heat flux are identical at the plane of contact.

Solution In a case when there is an ideal contact between two bodies CD and ®, the heat flux and temperature equality occurs at the plane of contact (Fig. 14.10), therefore

1:11 x=o -T - 2 Ix=o' A 81; 1

ax x=o

(1)

= A 81; 2

o

ax

x=o

x

Fig. 14.10. Diagram of two touching bodies

r:

Temperature at the plane of contact does not change with time; this is why the temperature field is described for both bodies by (16) from Ex. 14.2, which was derived for the step-change in the half-space surface. Since within the plane of contact heat flux is formulated as (19) in Ex. 14.2; therefore, from (1), one obtains

Exercise 14.8 Depth of Heat Penetration

375

(2)

Since (2) is solved with respect to Ts ' one gets

T = s

~ ·~,o +~~C2P2 '1;,0 ~~CIPI +~~C2P2

(3) '

where T},O and T2,o are initial constant temperatures of both bodies. One can deduce from the analysis of (3) that the product ~ACP is a weight factor in (3), which has an influence on whether the contact temperature T, is closer to temperature T},O or T2,o. If ~~CIPI > ~A2C2P2 ' then contact temperature is closer to temperature T} 0. Equation (3) is also true for bodies with finite dimensions, provided that the contact time is short. Equation (3) confirms the phenomenon, which is observed when one touches objects whose temperature is lower than the temperature of a human body. Wooden objects seem to be warmer than, for instance, objects made of metal or stone. In the case of wooden objects, product ~ACP is smaller than the product for human body. The sensory impression one gets is that the object made of wood is warmer than the object made of metal. In reality, both objects have the same temperature; the only thing that differs is the contact temperature T,

Exercise 14.8 Depth of Heat Penetration Determine the depth of heat penetration inside a body with a step-change in the half-space surface temperature. As a penetration depth x = 5, assume a coordinate point in which temperature change To - T(5, t) constitutes 1% of the difference (To - T), where To and T, are, respectively, the initial and surface temperature. On the basis of the obtained formula, determine a time interval 0 S t s tv in which a steel wall of a tank, cooled one-sided by water, can be treated as a semi-infinite body. For the calculation use the data that comes from the emergency cooling of a pressure ves5 2/s. sel of a nuclear reactor: To = 350°C, T, = 20°C, a = 1.1.10- m The thickness of the vessel wall is L = 0.2 m. Calculate the vessel's wall temperature after time tL at a distance of ~ = 50 mm from the vessel's inner surface.

376


Solution Here, we will make use of (16) from Ex. 14.2 for temperature distribution in the half-space

T(x,t)-J: To -T:

=erf(_X_).

(1)

2f;i

From the definition of the depth of heat penetration, we have

To -T(8,t)=0.01(To -Ts )

,

(2)

from where, we get

T(8,t)-Ts

(To -t; )

= 0.99.

From table in Appendix A for

erf[ 2~ )

(3)

= 0.99

we obtain

8

(4)

C=I.82.

2va l

The depth of heat penetration is determined from (4)

(5)

8=3.64f;i. Time t L is determined from (5) after substituting 8 =L L

= 3.64~atL'

IL

=~

()2 1 0.2 =2745 s. (.L:)2= 1.1·103.64

a 3.64

5

Temperature at a distance x =

•

~

T( 8p 1L ) =I: + (To - I: )erf[ =20+(350-20)erf(

after time t L is

~) =

2v al L

~

0.05 )= 2 1.1.10-5 ·274.5

= 20 + 330erf (0.455) = 20 + 330·0.48007 = 178.4°C.

Exercise 14.9 Calculating Plate Surface Temperature Under the Assumption

377

Exercise 14.9 Calculating Plate Surface Temperature Underthe Assumption that the Plate is a Semi-Infinite Body Thick steel plate was quickly placed into an industrial furnace at high temperature. Furnace temperature Tp is much higher than the plate surface temperature Ts , i.e. Tp » Ts . One can assume, therefore, that the plate surface was suddenly warmed by a heat flow with constant density qs' since 4 4 Tp >>Ts • Treat the plate as a semi-infinite body. Calculate plate surface temperature and temperature at point x = 0,03 m under the plate surface. 2 Assume that heat flux is qs = 500000 W/m , initial plate temperature To = 30°C, A = 40 W/(m·K), C = 460 J/(kg·K), p = 7770 kg/m', Calculate temperature after time t = 30 s, from the moment the charge is placed in the furnace.

Solution Surface temperature is expressed by (12) in Ex. 14.3: T, =

TL-o = To + -

2Qs Ji = 30 + 2· 500000.J30 = 288.4° C . ~ffACP ~ff·40·460·7770

l

Temperature at the point with a coordinate x is given by (11), Ex. 14.3:

T(x,t) =To + ~ [2~e-X2/(4at) -x[l-erf[ 2~ ))

where

a= c:·

After substitution of the numerical values, one obtains

a=~= cp

x

40

460·7770

=1.11913.10-5 m 2js,

0.03

2~ 2"'1.11913.10-5 ·30

=0.81863.

From Appendix A, one has

erf'(0.81863) = 0.753. After substituting data into temperature formula, one gets

T(0.03 m; 30 s)=30+

50~~00[2 1.11913~10-5 ·30 .e-0818632 _

-0.03(1- 0.753) ] = 30 + 39.6 = 69.6°C.

378


Exercise 14.10 Calculating Ground Temperature at a Specific Depth Water-main pipe is buried in the ground at a depth of x = 1.2 m. Initial ground temperature measures To = 5°C. External air temperature has dropped to Tez = -15°C and remained constant for 50 days. Air-to-ground 2·K). surface heat transfer coefficient is at a = 10 W/(m Calculate ground temperature at a depth of x = 1.2 m. Assume the following ground proper7 2/s. ties for the calculation: A = 2.5 W/(m·K), a = 3.10- m

Solution First, dimensionless numbers F0 and Bi will be calculated at 3.10-7 ·50·24·3600 Fo = - 2 = 2 = 0.90, x 1.2 Bi= ax = 10·1.2 =4.8 A 2.5 '

~

2vFo

~ =0.5270,

BiJF; =4.8~0,9 =4.5537.

2 0.90

Temperature at a depth of x Ex. 14.4

= 1.2 m will be calculated using 1

) =To + ( 1;;z -To ){ I-erf ( 2JF; T (x,t

)

-e

(Bi+Bi

(12) from

2Fo)

x

x[I-erf(2~ +BiJF;)]} = = 5 +( -15 - 5){1- erf (0.527) - e(4.8+20.7362) [1- erf (0.527 + 4.5537)]} = 5 - 20{I- erf(0.527)_e2S.S362 [1- erf'[ 5.0807)]}. Once the value of function erf is read from Appendix A in Table AI, one has

T (x,t) = 5 - 20{ 1- 0.54389 -1.230676 .10 11 [I-I]} = -4.12° C. The obtained result is not, however, accurate due to the fact that it is difficult to calculate the product e25,5362 . erf (5.0807), since function erf (5.0807) is very close to unity and is not tabulated for an argument larger than 3 (Appendix A). This is the reason why temperature T(x, t) is obtained by means of the MathCAD program, in which the function erf (z) is also

Exercise 14.11 Calculating the Depth of Heat Penetration in the Wall

379

calculated for arguments larger than z = 3. Once calculations are completed, one has T (x, t) =-2.47°C. Similar temperature values are obtained from diagrams presented in Figs. 14.4 and 14.5 (Ex. 14.4). It is evident from the calculations above that one should bury the pipe at a greater depth than it is suggested in this exercise, so that one can avoid the danger of water freezing inside the pipe.

Exercise 14.11 Calculating the Depth of Heat Penetration in the Wall of a Combustion Engine Rotational speed of a two-stroke spark-ignition engine is 2200 rev.lmin. The amplitude of temperature fluctuations on the inner cylinder surface is 5.7 K. Calculate penetration depth of temperature oscillations in the cylinder wall. Cylinder is made of a cast iron with the following thermo5 2/s. physical properties: A =52 W/(m·K), a = 1.7.10- m

Solution Penetration depth is given by (29), Ex. 14.6:

Xw=4.605~ .

(1)

Frequency of temperature changes is calculated using formula 2Jr -n 0)=--

60

rad/s,

(2)

where n rev.lmin is the rotational speed of the engine shaft. After substituting (2), one has 0)

= 2Jr' 2200 = 230.38

rad/s.

60 Penetration depth of temperature oscillations, determined by means of (1), is X

w

= 4.605

5

2 ·1.7 .10230.38

=1.769.10-3 m =1.769 mm.

It is evident, therefore, that temperature fluctuations on the cylinder surface are quickly suppressed and do not penetrate the cylinder wall deep enough.

380


Exercise 14.12 Calculating auasi-Steady-State Ground Temperature at a Specific Depth when Surface Temperature Changes Periodically In the summer, ground surface temperature changes from 35°e to 100 e within 24 hours. Assuming that similar temperature changes occur over a longer period of time, so that steady-state temperature fluctuations are formed underground, calculate temperature change intervals at a depth of a) Xl = 0.9 m and b) x2 = 1.2 m. Also determine phase shift and time-lag of temperature changes at a depth Xl and x 2 in relation to temperature changes on the ground surface. Assume the following thermo-physical properties of the ground (clay) for the calculation: A, = 1.28 W/(m·K), C = 880 J/(kg·K), p = 1500 kg/m',

Solution Formulas derived in Ex. 14.6. will be used to solve this exercise. Amplitude of temperature changes is given by (26), Ex. 14.6

Tm{x,t)-f =e-x~ I1T

(1)

'

where: ~T ==

T

-T.

max

mIll

2

-

amplitude of ground surface temperature changes,

Tm ax - maximum temperature of ground surface in °C, Tmin - minimum temperature of ground surface in °C, - T +T. T == max mIll - average ground temperature. 2 Ground temperature fluctuations at a depth X occur in the interval

f -I1Te-x~ ~ t; (x,t) ~ i +I1Te-x~. A phase shift in temperature fluctuations at a depth Ex. 14.6))

rp=x{jf,

(12) X

is ((13) from (3)

while time-lag I1t, which corresponds to angle tp is

x{jf

g; x~o

tp I1t-----x ---- - OJ - OJ

2a -

2 OJa - 2 Jra'

(4)

Exercise 14.12 Calculating Quasi-Steady-State Ground Temperature

381

where OJ = 21C/to stands for temperature circular frequency, to- temperature change period. Calculations will be done separately for both Xl and x 2 • a) X

= Xl = 0.9 m.

a = ~ = 1.28 = 9.697 .10-7 cp 880·1500

~T=35-10 =25 =12.5 2

f

2

fi

2

/s,

0C

'

= 35+10 =22SC, 2

OJ =

2Jr =

to

2Jr = 7.2722.10-5 rad/s, 24·3600

~Te-XI.JmI2a =12.5ex

5

(-0.9

P

7.2722.10- ]=0.05 0 C . 2.9.697 .10- 7

Temperature fluctuations at a depth

Xl

= 0.9 m are in the interval

22.45°C ~ T; (Xl't) ~ 22.55°C . Time-lag in temperature fluctuations with respect to temperature changes on the ground surface amounts to

~t = 0.9 2

24·3600 = 75783.7 s = 21 h 3min. .10- 7

1C' 9.697

b)x=x2 = 1 . 2 m , 5

i1Te-X2.JmI2a =12.5exP(-1.2

7.2722.10- ]=0.008 0 C . 2.9.697.10-7

Temperature fluctuations at a depth x 2 = 1.2 m are in the interval 22.492° C ~ t; (x2 , t ) ~ 22.508° C . Time-lag I1t amounts to

I1t=~ 2

24·3600 7 =101044.9 s=28 h 4min. ·10-

1C'9.697

382


From the analysis of results obtained for both cases, one can discern that temperature fluctuations, which occur on the ground surface are very quickly suppressed. Temperature changes that occur underground at a depth of x t = 0.9 m and x2 = 1.2 m are considerably delayed in comparison with the changes that occur on the ground surface.

Exercise 14.13 Calculating Surface Temperature at the Contact Point of Two Objects Calculate surface temperature at the point of contact of a chamotte brick heated to a temperature of 200°C with a) a cast iron object, b) a wooden object (oak), with a temperature of 20°C. Lets assume that the objects are suddenly placed against the heated chamotte brick. Assume that the contact between the two objects is ideal, i.e. the temperature and heat flux on the contact surface are identical. Use the following thermo-physical properties of the materials for the calculation: • chamotte brick: A =0.9 W/(m·K), C = 835 J/(kg·K), p = 1800 kg/m', • cast iron: A =53 W/(m·K), C =545 J/(kg·K), p =7200 kg/m', • oak wood: A= 0.19 W/(m·K), C = 2400 Jz(kg-K), p= 700 kg/rn'.

Solution Temperature of the surfaces in contact with each other will be calculated from (3), Ex. 14.7 T s

= ..p:;;:;;:·1;,0 + ~~ C2P2 • 1;,0 ~A,C1Pl +~~C2P2

(1) •

After substitution, of the numerical values we have a) chamotte brick-cast iron T = ,",,0.9· 835·1800 ·200 + ,",,53. 545·7200· 20 = 33.43 0 C , s -J0.9 .835 ·1800 + -J53 ·545 . 7200

b) chamotte brick-oak wood

Literature

T

= .J0.9· 835 ·1800 · 200 + .J0.19· 2400· 700· 20 =141.15

s

383

0C.

~0.9. 835·1800 + ~0.19· 2400·700

From the comparison of the obtained results, it is clear that the contact temperature is closer to the initial temperature of the body with a higher product value ACp. In the case of a) contact temperature T, is closer to the initial temperature of the cast iron, while in the case of b) to the initial temperature of the chamotte brick.

Literature 1. Carslaw HS, Jaeger JC (1986) Conduction of Heat in Solids. Clarendon Press,

Oxford 2. Janke E, Emde F, Losch F (1960) Tafeln hoherer Funktionen. Teubner, Stutt-

gart 3. Kulish VV, Dallas JL (2000) Fractional- diffusion solutions for transient lo-

4. 5. 6. 7.

8.

cal temperature and heat flux. Transactions of the ASME, Journal of Heat Transfer 122: 372-376 Tautz H (1971) Warmeleitung und Temperaturausgleich. Verlag Chemie, Weinheim (1999) The Heat Transfer Problem Solver. Research and Education Association. New Jersey, Piscataway Thomson WJ (1997) Atlas for Computing Mathematical Functions. WileyInterscience Publication, John-Wiley and Sons, New York ,[(HTKHH BA, IlpYIl:HHKOB All (1975) Onepauonaoe MCQHCJIeHHe. BbICIIIajI IllKoJIa,MocKBa JIbIKOB AB (1967) TeOpHjI TerrJIorrpOBOIl:HOCTH. BbICIIIajI lIIKoJIa, MHHCK


This chapter analyzes the phenomenon of transient heat conduction in simple-shape bodies. It presents twenty exercises, which contain both, theory and computational problems. Using the separation of variables method and Laplace transform, the authors derive formulas for temperature distribution in a plate, cylinder and sphere with boundary conditions of 1st, 2nd and 3rd kind. Also develop computational programs as well as graphs and diagrams, which enable one to calculate roots of characteristic equations, temperature distribution, temperature change rate and average temperature. Dimensionless teperature values in the function of time are listed for boundary conditions of 2nd kind in tables provided. Derived formulas are applied to the calculation of temperature transients and thermal stresses.

Exercise 15.1 Formula Derivation for Temperature Distribution in a Plate with Boundary Conditions of 3rd Kind Derive a formula for temperature distribution in a plate with a thickness 2L, when convective heat transfer occurs between both plate surfaces and the surroundings, with temperature Tcz' when heat transfer coefficient a is constant. Initial plate temperature is constant and is To (Fig. 15.1). Assume constant material properties for the calculation: A, c and p.

Solution Plate temperature distribution is described by the heat conduction equation

aT

a2T

at

ax

-=a2

boundary conditions

O~t, '

O~x~L,

(1)

386


aT

ax

-:i aTI

ax x=L

x=o

=

O~t

=0

I

,

(2)

'

a(TIX=L - ~z)'

O~t

(3)


T(x,t)lt=o

= To,

O~x~L.

(4)

T

Fig. 15.1. Heating an infinitely long uniformly thick plate

Due to the symmetry of the problem, only region 0 :s x:S L (a half of the plate's thickness) is analyzed here. In order to reduce the boundary condition (3) to a homogeneous condition, a new variable is introduced e(x,t)=T(x,t)-~z .

(5)

The initial-boundary problem (1)-(4) can be written then in the following way:

to at

a2e ax '

(6)

ael

=0

(7)

-=a2

ax x=O

'


OBI a

-,.1,-

X x=L

=aB! x=L'

387

(8)

(9)

The separation of variables method is used to solve problems (6)-(9); according to this method, the solution has a form

B(x,t) = tp(t )V/( x).

(10)

Once (10) are substituted into (6), one obtains 2

1 de: d V/ -V/-=tp-. a dt dx'

(11)

Once both sides of (11) are divided by (lj/,tp) can be written in the form 1 1 de: _ 1 d V/ ---; tpdt - V/ dx 2 • 2

(12)

Due to the fact that the equality (12) should occur for any value of x and t, both sides of the equation should be equal to the constant, which should, in turn, have a negative value due to a finite temperature value in time. Once the constant is marked as -k', one has 2

1 1 d.p _ 1 d 1f/ _ k 2 a tp dt - V/ dx 2 - - ,

(13)

from which two equations follow:

dqJ +ak 2qJ=O, dt d2

~+k2V/=O. 2 d t

(14)

(15)

General solutions to (14) and (15) are functions (16) V/ = C2 cos ( kx) + C3 sin ( kx) . Once (16) and (17) are substituted into (10), one obtains

(17)

388

15 Transient Heat Conduction in Simple-Shape Elements ak 2t

B = tp(t)V!(x) = e-

[Acos(kx) + Bsin(kx)] ,

(18)

where A = C 1C2 and B = C1C3• From boundary condition (7), one obtains

o() ox

= e -ak

I

2t

k (-A sin 0 + B cos 0) = 0 ,

x=o

hence, B = O. Therefore, the solution of (18) has the following form

B( x,t) = Ae-aet cos( kx).

(19)

Once (19) is substituted into boundary condition (8), one has

AkAe-aet sin ( kL) = a Ae-aet cos ( kL) , hence the equation

kL ctg(kL) = aL ·

(20)

A Once we denote aLIA = Bi and kL = 11, transcendental (20) can be written in the form

ctgzz =

;i·

(21)

Equation (21) has an infinite number of roots, which can be determined using one of the methods for solving non-linear algebraic equations, either, for instance, the interval halving method or Muller method [1, 2]. These are iterative methods; when using them, one is required to give an approximate starting value for each element or interval in which a particular element is found. The interval with element Jli can be determined and presented in a graphical form. Once we denote Y1 = ctg Jl and Y2 = ulbi, we can easily determine roots of (21), if we define intersection points of functions y/p) and Y2{J1) first (Fig. 15.2). One can see that a different set of roots corresponds to every value of Biot number Bi

111 < 112 < 113 < ... < I1 n < ...


389

Y Yl

=

ctgrz Yl

Yl

Yl

Fig. 15.2. Graphical determination of roots of characteristic equation (21): ctg fl = fl/Bi

For number Bi (21) are fll

~

co line Y2

=u/Bi overlaps the x-axis

135 /13 ==-lC, ... , 222

==-lC , fl2 ==-lC ,

fln==

and the roots of

(2n - l)n/2, n == 1,2,3....

For Bi ~ 0 line Y2 = u/Bi overlaps the y-axis and the roots of (21) are = 0, fl 2 = x, /1 3 = 2n ... /1 n = (n - l)n, n = 1, 2, 3... It is clear, therefore, that i-element lies in the interval

fl]

i =1,2, ...

(22)

Program in FORTRAN language for calculating roots of the characteristic equation (21) by means of interval halving method C

Calculating roots of characteristic equation program p15_1 dimension eigen(50) open(unit=l,file='pI5 l.in') open(unit=2,file='pI5_I.out') read(l,*)ne

390

15 TransientHeat Conduction in Simple-Shape Elements write(2,' (a) ') "CALCULATING ROOTS OF CHARACTERISTIC &EQUATION" write (2, , (/a) ') "DATA ENTERED" write(2,' (a,ilO) ') "ne =",ne write(2,' (/a,i3,a) ') "CALCULATIONS OF PRIMARIES",ne, &" ROOTS OF EQUATION X*TAN(X)=BI" write(2,' (/a) ')"CALCULATED EQUATION ROOTS" write(2,' (a,a) ')" Bi mil mi2 mi3 ", &" mi4 mi5 mi6" Bi=O. call equation_roots (Bi,ne,eigen) write(2,' (f7.3,5x,6f9.4) ') Bi, (eigen(i),i=l,ne) Bi=O.OOl variable=O.OOl to k=1,5 to j=1,9 call equation roots (Bi,ne,eigen) write(2,' (f7.3,5x,6f9.4) ') Bi, (eigen(i),i=l,ne) Bi=Bi+variable enddo variable=variable*lO. enddo call equation_roots (Bi,ne,eigen) write(2,' (f7.3,5x,6f9.4) ') Bi, (eigen(i),i=l,ne) end program p15 1

c c c c

procedure calculates roots of characteristic equation x*tan(x)=Bi where Bi is Biot number, ne the number of calcul. roots, eigen vector with recorded calculated roots subroutine equation_roots (Bi,ne,eigen) dimension eigen(*) pi=3.141592654 to i=l,ne xi=(float(i)-l.)*pi xf=pi*(float(i)-.5) to while (abs(xf-xi) .ge.5.E-06) xm=(xi+xf)/2. y=xm*sin(xm)/cos(xm)-Bi if (y.lt.O.) then xi=xm else xf=xm endif enddo eigen(i)=xm enddo return end


391

The first six roots of (21) are presented in Table 15.1. Every root JLi corresponds to a single (19), which has the following form, if we take into account that JLi = k1L: i = 1, 2 ...

(23)

The obtained solution (23) satisfies differential equation (1) for any i, but does not satisfy the initial condition, since for t = 0 (23) has the form i = 1,2 ...

(24)

It is easy to satisfy the initial condition T(x,O) = To(x), if we assume that the solution for temperature distribution is the sum of partial solutions (24) (25) Constants A n will be determined from the initial condition. Once both sides

of the (25) are multiplied, for t

=0, by

cos( Am

~)

and then integrated in

the interval 0 :::; x :::; L, one obtains

00 fCOS(Jlm o

!"')dx = ffA nCOS(JLn !...)COS(Jlm !-)dX. L L L

(26)

0 n=l

Noting that

fCOs(JLn ~ }OS(JLm ~)dx = 0,

gdy n oF m ,

(27)

then from (26), one has

° fCOS(JLn ~)dx 0

Oo~sinJLn =A JL n

n

An fCOS (JLn ~)dx , 2

=

L[I+_I-sin2 JLn) , 2 2JLn

(28)

(29)

392


Table 15.1. Roots of characteristic equation ctgz, =plBi Bi 0.000 0.001 0.002 0.003 0.004 0.005 0.006 0.007 0.008 0.009 0.010 0.020 0.030 0.040 0.050 0.060 0.070 0.080 0.090 0.100 0.200 0.300 0.400 0.500 0.600 0.700 0.800 0.900 1.000 2.000 3.000 4.000 5.000 6.000 7.000 8.000 9.000 10.000 20.000 30.000 40.000 50.000 60.000 70.000 80.000 90.000 100.000

0.0000 0.0316 0.0447 0.0547 0.0632 0.0706 0.0774 0.0836 0.0893 0.0947 0.0998 0.1409 0.1723 0.1987 0.2218 0.2425 0.2615 0.2791 0.2956 0.3111 0.4328 0.5218 0.5932 0.6533 0.7051 0.7506 0.7910 0.8274 0.8603 1.0769 1.1925 1.2646 1.3138 1.3496 1.3766 1.3978 1.4149 1.4289 1.4961 1.5202 1.5325 1.5400 1.5451 1.5487 1.5514 1.5535 1.5552

3.1416 3.1419 3.1422 3.1425 3.1429 3.1432 3.1435 3.1438 3.1441 3.1445 3.1448 3.1479 3.1511 3.1543 3.1574 3.1606 3.1637 3.1668 3.1700 3.1731 3.2039 3.2341 3.2635 3.2923 3.3204 3.3477 3.3744 3.4003 3.4256 3.6436 3.8088 3.9352 4.0336 4.1116 4.1746 4.2264 4.2694 4.3058 4.4915 4.5615 4.5979 4.6202 4.6353 4.6461 4.6543 4.6606 4.6658

6.2832 6.2833 6.2835 6.2837 6.2838 6.2840 6.2841 6.2843 6.2845 6.2846 6.2848 6.2864 6.2880 6.2895 6.2911 6.2927 6.2943 6.2959 6.2975 6.2991 6.3148 6.3305 6.3461 6.3616 6.3770 6.3923 6.4074 6.4224 6.4373 6.5783 6.7040 6.8140 6.9096 6.9924 7.0640 7.1263 7.1806 7.2281 7.4954 7.6057 7.6647 7.7012 7.7259 7.7438 7.7573 7.7679 7.7764

9.4248 9.4249 9.4250 9.4251 9.4252 9.4253 9.4254 9.4255 9.4256 9.4257 9.4258 9.4269 9.4280 9.4290 9.4301 9.4311 9.4322 9.4333 9.4343 9.4354 9.4460 9.4565 9.4670 9.4775 9.4879 9.4983 9.5087 9.5190 9.5293 9.6296 9.7240 9.8119 9.8928 9.9667 10.0339 10.0949 10.1502 10.2003 10.5117 10.6543 10.7334 10.7832 10.8172 10.8419 10.8606 10.8753 10.8871

12.5664 12.5665 12.5665 12.5666 12.5667 12.5668 12.5668 12.5669 12.5670 12.5671 12.5672 12.5680 12.5688 12.5696 12.5703 12.5711 12.5719 12.5727 12.5735 12.5743 12.5823 12.5902 12.5981 12.6060 12.6139 12.6218 12.6296 12.6375 12.6453 12.7223 12.7967 12.8678 12.9352 12.9988 13.0584 13.1141 13.1660 13.2142 13.5420 13.7085 13.8048 13.8666 13.9094 13.9406 13.9644 13.9830 13.9981

15.7080 15.7080 15.7081 15.7082 15.7082 15.7083 15.7083 15.7084 15.7085 15.7085 15.7086 15.7092 15.7099 15.7105 15.7111 15.7118 15.7124 15.7131 15.7137 15.7143 15.7207 15.7270 15.7334 15.7397 15.7461 15.7524 15.7587 15.7650 15.7713 15.8336 15.8945 15.9536 16.0107 16.0654 16.1177 16.1675 16.2147 16.2594 16.5864 16.7691 16.8794 16.9519 17.0026 17.0400 17.0686 17.0911 17.1093


393

hence, one can easily determine constant An

An

Zsin zz,

= ()o - - - .- - - JL n + SIn JL n COS JL n

(30)

By substituting (30) into (25), the expression that defines temperature distribution is obtained _

() at2 x -f.in2 L cos fJn - e · n=l JL n + SIn JLn COS JLn L 00

2 SIn . JL n

B(x,t)-BoL.

(31)

If we introduce a dimensionless coordinate X = x/L and Fourier number 2 Fo = at/L , then we can write the (31) in the following form

~= T(x,t)-I;;z ()o

To - I;;z

=2f

sinfJn.coS(fJn X ) e-/1;Fo.

(32)

n=l JLn + SIn JLn COS JLn

When calculating thermal stresses and accumulated or given off energy during the processes of heating and cooling, respectively, one needs to know what the average temperature across the plate thickness is (33) where B(x,t) is given by (32). Once (31) is substituted into (33) and subsequently integrated, one has (34)

The case of an infinitely large heat transfer coefficient a When heat transfer coefficient a is very large, the plate surface temperature is very close to the temperature of a medium. In the case when a ~ 00, then 71x=±L = Tez· If the Biot number Bi = aUA> 100, one can assume that the heat transfer coefficient is infinitely large. For a ~ 00 the roots of characteristic equation (21) are (Fig. 15.1)

n=l, 2, ...

(35)

394


Equation (32) assumes the form then

hence, one obtains

-B =-4~(-lr+I LJ

°

Jr n=l

0

(2n -1)

cos

[(2n-l)Jr] X exp [(2n-l)2 - - - Jr 2

2

Fo] .

(37)

2

Average temperature across the plate thickness is

o 1 L -=-fBdx=

° 0

LOo0

L (2n -1)8 00

n=l

2n - )2 Jr 2Fo] .

[ ( 1 exp - - -

2 Jr2

(38)

2

Equations (37) and (38) define plate temperature with the boundary condition of 1st kind, when there is a step increase in plate surface temperature from the initial temperature To to temperature Tcz .

Exercise 15.2 A Program for Calculating Temperature Distribution and Its Change Rate in a Plate with Boundary Conditions of 3rd Kind Write a program in the FORTRAN language for calculating plate temperature distribution, using the formulas derived in Ex. 15.1. The program should also enable one to calculate average temperature and temperature change rate at any point across the plate thickness. Use the developed program to calculate the inner and surface temperature transient of the plate, whose thickness is 2L (Fig. 15.1). Also calculate temperature change rate on the surface of and inside the plate thickness. Assume the following val5 2/s, ues for the calculation: L = 0.1 m, A. = 50 W/(m·K), a = 1.10- m 2·K), a = 1000 W/(m To = 20°C, Tcz = 100°C.

Exercise 15.2 A Program for Calculating Temperature Distribution

395

Solution Formulas for temperature distribution T(x,t) and average temperature within the plate thickness f (x,t) were already derived in Ex. 15.1. Temperature change rate is obtained once (32), from Ex. 15.1, is differentiated with respect to time.

dT(x,t) _ 2a ( Tcz 2 dt L

7')

10

00

"

. f.1n f.1 n2 SIn

LJ n=l

f.1 n

cos

(XJ L f.1n -

+ sin f.1 n cos f.1 n

2

at

-Pn L2

e.

(1)

Program for calculating temperature distribution in a plate with thickness L, which undergoes convective heating or cooling on its front face and is thermally insulated on the rear surface C C C C

Calculating temperature distribution in a plate with thickness L convectively heated or cooled on the butting face and thermally insulated on the rear surface program p15_02 dimension eigen(50) open(unit=1,file='p15 02.in') open(unit=2,file='p15 02.out') read(l,*)ne read(l,*)t_o,t_cz,s_l,s a read(l,*)s_lam,s_alfa write(2,' (a) ') "CALCUL. PLATE TEMPERATURE DISTRIBUTION" write (2, , (/a) ') "INPUT DATA" write(2,' (a,ilO) ') "ne =",ne write(2,' (a,elO.5,a) ') "t ° =",t_o," [C]" write(2,' (a,elO.5,a) ') "t cz =",t_cz," [C]" write(2,' (a,elO.5,a) ') "1 =",s 1, " [m]" write(2,' (a,elO.5,a) ') "a =",s a, " [m"'2/s]" write(2,' (a,elO.5,a) ') "lambda =",s_lam," [W/mK]" write(2,' (a,elO.5,a) ') "alfa =",s alfa," [W/m2K]" Bi=s - alfa*s lis lam call equation_roots (Bi,ne,eigen) write(2,' (/a) ')"CALCULATED TEMPERATURE [C]" wr i te (2, , (a, a) , ) &" t[s] T(O,t) T(l,t) T sr(t) dT/dt(O,t)", & dT/dt(l,t)" t=O. to while (t.le.2000.) write(2,' (f5.0,5(3x,elO.3)) ')t,

396

15 TransientHeat Conduction in Simple-Shape Elements & temperature(O.,t,t_cz,t_o,s_l,s_a,ne,eigen), & temperature (s_l,t,t_cz,t_o,s_l,s_a,ne,eigen) , & temperature_sr(t,t_cz,t_o,s_l,s_a,ne,eigen), & temperature szyb(O.,t,t_cz,t_o,s_l,s_a,ne,eigen), & temperature szyb(s l,t,t cZ,t o,S l,s a,ne,eigen) t=t+5. enddo end program p15 02

c

according to equation (1) function temperature szyb(x,t,t cZ,t o,S l,s a,ne, & eigen) dimension eigen(*) teta=O. to i=l,ne s=eigen(i) teta=teta+s**2*sin(s)*cos(s*x/s 1)* & exp(-s**2*s a*t/s 1**2)/(s+sin(s)*cos(s)) enddo temperature_szyb=2.*s a*(t cz-t o)*teta/s 1**2 end function

c

according to equation (34) in Ex. 15.1 function temperature sr(t,t cz,t_o,s l,s a,ne,eigen) dimension eigen(*) teta=O. do i=l,ne s=eigen(i) teta=teta+sin(s)*sin(s)* & exp(-s**2*s a*t/s 1**2)/(s+sin(s)*cos(s))/s enddo temperature_sr=t cz+(t o-t cz)*2.*teta end function

c

according to equation (31) in. Ex. 15.1 function temperature(x,t,t cZ,t o,S l,s a,ne,eigen) dimension eigen(*) teta=O. do i=l,ne s=eigen(i) teta=teta+sin(s)*cos(s*x/s 1)* & exp(-s**2*s a*t/s 1**2)/(s+sin(s)*cos(s)) enddo temperature=t cz+(t o-t cz)*2.*teta end function

c c c c

procedure calculates roots of the characteristic equation x*tan(x)=Bi where Bi is Biota number, ne number of calculated roots, eigen output vector with calculated roots


397

subroutine equation_roots (Bi,ne,eigen) dimension eigen(*) pi=3.141592654 do i=l,ne xi=(float(i)-l.)*pi xf=pi*(float(i)-.5) do while (abs(xf-xi) .ge.5.E-06) xm=(xi+xf)/2. y=xm*sin(xm)/cos(xm)-Bi if (y.lt.O.) then xi=xm else xf=xm endif enddo eigen(i)=xm enddo return end

Temperature transients of the plate surface, T(L,t) and T(O,t) and average temperature T(t) are presented in Fig. 15.3. Temperature change rates

dT/dt of the plate front face (x = L) and the rear surface (x tion of time are shown in Fig. 15.4.

=0) in the func-

100~-----------------.,

T[OC]

80

60

40

400

800

1200

1600 t [s] 2000

Fig. 15.3. Temperature transients of a front T(L,t) and rear plate surfaces T(O,t) and average temperature T (t )

398

15 Transient Heat Conduction in Simple-Shape Elements 0,25 ~-----------------,

dT/dt [KIs] 0,20

0,15

x=L 0,10

0,05

0,00 ,"""",,-~----'-_....I....o 400 800

I......---,,-----&..._....a..-_ _~

1200

1600 t [s] 2000

Fig. 15.4. Heating rate transient dT/dt of the front plate face (x surface (x = 0)

= L) and the rear

Exercise 15.3 Calculating Plate Surface Temperature and Average Temperature Across the Plate Thickness by Means of the Provided Graphs Determine front face temperature of a steel plate and the temperature of its insulated rear surface (Fig. IS.5) by means of the attached diagrams [I, 2]. Also calculate average plate temperature. The front face heated to an initial temperature of To = 100°C is suddenly cooled by a compressed air flow whose temperature is Tcz = 20°C. Use the following data for the calcula5 2·K), L = 0.05 m, A = 50 W/(m·K), a = AI(c ) = 1.10tion: a = 200 W/(m 2/s, m t = 250 s. Furthermore, calculate the insulated plate surface temperature, if heat transfer coefficient is infinitely large, i.e. if a ~ 00. Determine unknown temperatures by means of the program developed in Ex. 15.2.

Solution To find appropriate temperatures in the diagrams provided, the Biot and Fourier numbers are calculated first

Fo=:!!....= 1.10-

Bi= aL = 200·0.05 =0.2

A

50

'

L2

5

·250 =1.

0.05

Exercise 15.3 Plate Surface Temperature and Average Temperature

T

399

+ a

T(O,t)

air flow

thermal insulation ._.~

X

Fig. 15.5. Air flow cooling of the steel plate

From diagram in Fig. 15.6, one has (}/(}o =0.76, i.e.

T(L,t) - 1;,z = TCL,t) - 20 = 0.76 , To -~z To -20 hence, T (L, t) = 80.8°C. Temperature of the rear insulated surface is determined from Fig. 15.7 T(O,t) - 20 100-20

= 0.85 '

hence, one gets T(O, t) = 88°C. Average temperature T(t) is determined from the diagram in Fig. 15.8

TCt) - 1;,z

=

0.82

To -Tcz

'

hence, T(l) = 85.6°C. In a case when a

TCO,!) - 1;,z To -t;

~ 00,

from diagram in Fig. 15.9 one has

= 0.1 08 ,

which results in

T( 0,1) = 80·0.108 + 20 = 28.64°C. It is clear, therefore, that when a ~ 00 the plate cooling occurs much 2·K). Once calculations are completed by faster than when a = 200 W/(m means of the program from Ex. 15.2, one gets

400


T(L,t) = 82.1°C T(O,t) = 88.4°C

T(t)

= 86.3°C

T(O,t) = 28.7° C

In both cases, similar results are obtained. Diagrams help us easily determine temperature, but the method is less accurate, since the diagrams in Figs. 15.6-15.9 do not have a corresponding curve for every value of the Biot number.

Appendix 15.1. Diagrams for calculating plate temperature with a convective boundary condition (Figs. 15.6-15.8)

o 0~2

ft

()0 O~4

!

co ~-t--""'--+"7""'+--7"'f--r-+--:iM--+-t-1~~ooofo--lf-+-lo-++-4-+--I-++--++-+-I

08

.,--.t--7"I~r+---+-r--+-T-+-+-Ir--+r~I-I-~-A---,4--+--tlF---A--~ 0:6 f

I- fl 0,6 t--~---+-~--"'t----1 L>r~--M"-""!t-r-+'----ho£--+-,'-t-7-f-Jl--¥--r+-~+--¥--I 0..4 ()0

0,8 1.0 iiiI_~~~~8~~~iiiiiiiiii5~::::::L.LJ_l-Jo 5 0.. 1 0,2 0.. 5 1 2 5 10 20 50 100 200 500 1000 0.0012 5 0.. 01 2

Fo ----....

Fig. 15.6. A change in dimensionless temperature of the plate butting face 0(1, 2 Fo)l()o = [T(L,t) - TcJ/(To - Tc) in the Fourier number function Fo = atlL , Bi = aLIA

()

Bo 0..4

! 61---+----+---+-+-+--+---+-++-ItT-++l-++-+--tr-rt+-t-+---Y--rt-r--t-t~

t

0,

LO

OJ>012

5 0.01 2

5 0.1 0.2 0.5 1 2

5

10 20

0

50 100200 500 1000

Fo ---.....

Fig. 15.7. Dimensionless temperature changes in the center of the plate (insulated surface) O(O,Fo)IOo = [T(O,t) - TczJ/(To - Tc) in the Fourier number function Fo = 2 atlL , Bi = aLIA

Exercise 15.3 Plate Surface Temperature and Average Temperature

401

to

0 O~2

lJ

t

~ (t4

!

. ft 00

O~6

O~8

O~2

1,0 O~OOI

2

Fig. 15.8. Changes in dimensionless average" temperature 0 100 = [T(Fo) - T;;z] I (To - Tcz) in the Fourier number function Fo = aut:, Bi

= aLIA

xlL---"

Fig. 15.9. Temperature changes across the plate thickness for selected values of the Fourier number with a step-change in the plate surface temperature from tem2 perature To to temperature Tez' Fo = atlL , BI80 = [T(x,t) - TeJ/(To- Te)

402


Exercise 15.4 Formula Derivation for Temperature Distribution in an Infinitely Long Cylinder with Boundary Conditions of 3rd Kind Derive formulas for temperature distribution in an infinitely long cylinder with an outer surface radius r, when convective heat exchange takes place between a cylinder and its surroundings at temperature Tez and constant heat transfer coefficient a on the cylinder surface. Initial cylinder temperature is constant and is To. Assume, for the calculation, constant material properties: A~ c and p. T

Fig. 15.10. The heating of an infinitely long cylinder

Solution Temperature distribution in the cylinder is governed by the heat conduction equation (1)

by boundary conditions (2)

(3)


403


(4) where

B = T (r, t ) - T;;z ,

(5)

According to the separation of variables method, the solution of the initial-boundary problem will be searched for in the form

B(r,t) = cp(t )v(r).

(6)

By substituting dependency (6) into (1), one has

!~ dcp =~(d21f/ +.!.. dlf/). a

cp

V

dt

dr'

(7)

r dr

Since (7) should occur for any rand t, both sides of (7) should be equal to the constant, which should, in turn, have a negative value due to a finite value of temperature in time. By designating this constant as -k", one has (8)

hence, two equations follow

~ drp +ae =0,

(9)

21f/ d +.!.. dlf/ +k 21f/ = 0 . dr' r dr

(10)

cp

dt

A general solution of (9) and (10) are functions In 't' -

CIe-ak 2t ,

(11) (12)

Equation (6), therefore, has the form ak 2 / [

B = rp(t)lf/(r) = e-

AJo(kr) + BYo (kr)J,

(13)

404


Due to the condition (2) and by accounting for the fact that Yo(r) ~ 00: when r ~ 0, constant B in the (13) equals zero. Function (13) assumes the form (14) By substituting (14) into boundary condition, a characteristic equation is obtained (15) which results in

J o(krz )

Akrz

J} (krz )

arz

(16)

When (15) was derived, the following was accounted for

dIo (kr) dr

= -kJI (kr) .

(17)

Once notation Jl = kr is introduced, (16) has the form J o(Jl)

_ fi J} (fi) - m'

(18)

where Bi = arzIA. Equation (18) has an infinite number of roots. Figure 15.11 presents a graphical method for determining roots of the characteristic equation (18). Although such method is rarely used nowadays, it allows to find the intervals in which successive roots are found. One can deduce from Fig. 15.11 that the n-th root of this equation is located in the interval fid,n

where

fid,n and fig,n are

< fin < fig,n

'

(19)

the roots of the following equations

J} (fid) = 0,

(20)

t, (,llg ) = 0 ·

(21)

Zeros of Bessel functions J} and J o can be found in reference [5]. For Bi-sco the characteristic equation (18) assumes the form

Bi ~oo.

(22)


Likewise for Bi

~

405

0 (18) is simplified to a form Bi~O.

(23)

0,8

0,6

0,4 0,2

° -0,2 -0,4

4

2

-2 -4

-6

Fig. 15.11. Graphical method for determining roots of the characteristic equation (18): JO(Ji)IJ1(Ji) = p/Bi

406


Every root Jii corresponds to a one (14), which, if we take into account that rII. =k.r , has the following form: 1

I

Z

(24)

where R = rlr . The program in FORTRAN language helps to calculate roots of the characteristic equation (18). The first six roots of (18) are given in Table 15.2. Z

Program for calculating roots of the characteristic equation Jo{p)1J1(p) = piBi, Bi = a r z IA C

c

Program for calculating roots of the charact. (18) program p15_4 dimension eigen(50),zero(100) file p15_4.in is attached to the program open(unit=1,file='p15_4.in') open(unit=2,file='p15 4.out') read(l,*)ne read(l,*)nc read (1, *) (zero (i), i=l, 2*nc, 2) read(l,*) (zero(i),i=2,2*nc,2) write (2, , (a) ') & "CALCULATION OF ROOTS OF THE CHARACTERISTIC EQUATION" write(2,' (/a) ') "INPUT DATA" write(2,' (a,i10) ') "ne =",ne write(2,' (/a,i3,a) ') "CALCULATION OF FIRST",ne, & " ROOTS OF EQUATION X*J1(X)/JO(X)=BI" write (2, , (/a) ') "CALCULATED ROOTS" mi2 mi3 write(2,'(a,a)')" Bi mil ", & " mi4 mi5 mi6" Bi=O. call equation_roots_cyl(Bi,zero,ne,eigen) write(2,' (f7.3,5x,6f9.4) ') Bi, (eigen(i),i=l,ne) Bi=O.OOl zmienna=O.OOl do k=1,5 do j=1,9 call equation roots_cyl(Bi,zero,ne,eigen) write(2,' (f7.3,5x,6f9.4) ') Bi, (eigen(i),i=l,ne) Bi=Bi+zmienna enddo zmienna=zmienna*10. enddo call equation_roots cyl(Bi,zero,ne,eigen)

Exercise 15.4Formula Derivation forTemperature Distribution

407

write(2,' (f7.3,5x,6f9.4) ') Bi, (eigen(i),i=l,ne) end program pI5 4 c c c c c

procedure calculates roots of the characteristic equation x*JI(x)/JO(x)=Bi where Bi is Biot number, ne is number of calculated roots, eigen is output vector with calculated roots zero() is output vector with funct. JI(x) and JO(x) zeroing points see Fig.15.II subroutine equation_roots_cyl(Bi,zero,ne,eigen) dimension zero(*),eigen(*) pi=3.141592654 j=O do i=l,ne xi=zero(i+j) xf=zero(i+l+j) do while (abs(xf-xi) .ge.l.E-05) xm=(xi+xf)/2. y=xm*bessjI(xm)/bessjO(xm)-Bi if (y.lt.O.) then xi=xm else xf=xm endif enddo eigen(i)=xm j=j+I enddo return end

FUNCTION bessjO(x) REAL bessjO,x REAL ax,xx,z DOUBLE PRECISION pl,p2,p3,p4,p5,ql,q2,q3,q4,q5, & rl,r2,r3,r4,r5,r6,sl,s2,s3,s4,s5,s6,y SAVE pl,p2,p3,p4,p5,ql,q2,q3,q4,q5,rl,r2,r3,r4,r5,r6,sl,s2, & s3,s4,s5,s6 DATA pI,p2,p3,p4,p5/I.dO,-.1098628627d-2, .27345I0407d-4 &,-.2073370639d-5, .20938872IId-6/, qI,q2,q3,q4,q5/&.1562499995d-l, .1430488765d-3, -. 69III4765Id-5, &.7621095I6Id-6,-.934945I52d-7/ DATA rI,r2,r3,r4,r5,r6/57568490574.dO,-13362590354.dO, &65I619640.7dO,-112I4424.I8dO,77392.330I7dO, &-184.9052456dO/,sl,s2,s3,s4,s5,s6 &/575684904II.dO,1029532985.dO,9494680.7I8dO, &59272.64853dO,267.85327I2dO,I.dO/

408

15 TransientHeat Conduction in Simple-Shape Elements if(abs(x) .It.8.)then y=x**2 bessjO=(rl+y*(r2+y*(r3+y*(r4+y*(r5+y*r6)))))/ &(sl+y*(s2+y*(s3+y*(s4+y*(s5+y*s6))))) else ax=abs(x) z=8./ax y=z**2 xx=ax-.785398164 bessjO=sqrt(.636619772/ax)*(cos(xx)*(pl+y*(p2+y* &(p3+y*(p4+y*p5))))& z*sin(xx)*(ql+y*(q2+y*(q3+y*(q4+y*q5))))) endif return END FUNCTION bessjl(x) REAL bessjl,x REAL ax,xx,z DOUBLE PRECISION p5,ql,q2,q3,q4,q5,rl,r2,r3,r4, & pl,p2,p3,p4,r5,r6,sl,s2,s3,s4,s5,s6,y SAVE pl,p2,p3,p4,p5,ql,q2,q3,q4,q5,rl,r2,r3, & r4,r5,r6,sl,s2,s3,s4,s5,s6 DATA rl,r2,r3,r4,r5,r6/72362614232.dO,-7895059235.dO, &242396853.1dO,-2972611.439dO,15704.48260dO, &-30.16036606dO/,sl,s2,s3,s4,s5,s6/144725228442.dO, &2300535178.dO,18583304.74dO,99447.43394dO, &376.9991397dO,1.dO/ DATA pl,p2,p3,p4,p5/1.dO, .183105d-2,-.3516396496d-4, &.2457520174d-5,-.240337019d-6/, ql,q2,q3,q4,q5 &/.04687499995dO,-.2002690873d-3, .8449199096d-5, &-.88228987d-6, .105787412d-6/ if(abs(x) .It.8.)then y=x**2 bessjl=x*(rl+y*(r2+y*(r3+y*(r4+y*(r5+y*r6)))))/ &(sl+y*(s2+y*(s3+y*(s4+y*(s5+y*s6))))) else ax=abs(x) z=8./ax y=z**2 xx=ax-2.356194491 bessjl=sqrt(.636619772/ax)*(cos(xx)* &(pl+y*(p2+y*(p3+y* &(p4+y*p5))))-z*sin(xx)*(ql+y*(q2+y*(q3+y*(q4+y*q5))))) &*sign(l.,x) endif return END


Table 15.2. Roots of the characteristic equation Jo(j.1)IJ

j(j.1)

=j.1IBi, Bi = a r] A

Bi 0.000 0.001 0.002 0.003 0.004 0.005 0.006 0.007 0.008 0.009 0.010 0.020 0.030 0.040 0.050 0.060 0.070 0.080 0.090 0.100 0.200 0.300 0.400 0.500 0.600 0.700 0.800 0.900 1.000 2.000 3.000 4.000 5.000 6.000 7.000 8.000 9.000 10.000 20.000 30.000 40.000 50.000 60.000 70.000 80.000 90.000 100.000

0.0000 0.0447 0.0632 0.0774 0.0894 0.0999 0.1095 0.1182 0.1264 0.1340 0.1412 0.1995 0.2440 0.2814 0.3143 0.3438 0.3709 0.3960 0.4195 0.4417 0.6170 0.7465 0.8516 0.9408 1.0184 1.0873 1.1490 1.2048 1.2558 1.5994 1.7887 1.9081 1.9898 2.0490 2.0937 2.1286 2.1566 2.1795 2.2880 2.3261 2.3455 2.3572 2.3651 2.3707 2.3750 2.3783 2.3809

3.8317 3.8320 3.8322 3.8325 3.8327 3.8330 3.8333 3.8335 3.8338 3.8341 3.8343 3.8369 3.8395 3.8421 3.8447 3.8473 3.8499 3.8525 3.8551 3.8577 3.8835 3.9091 3.9344 3.9594 3.9841 4.0085 4.0325 4.0562 4.0795 4.2910 4.4634 4.6019 4.7131 4.8033 4.8772 4.9384 4.9897 5.0332 5.2568 5.3410 5.3846 5.4112 5.4291 5.4419 5.4516 5.4592 5.4652

7.0156 7.0157 7.0159 7.0160 7.0162 7.0163 7.0164 7.0166 7.0167 7.0169 7.0170 7.0184 7.0199 7.0213 7.0227 7.0241 7.0256 7.0270 7.0284 7.0298 7.0440 7.0582 7.0723 7.0864 7.1004 7.1144 7.1282 7.1421 7.1558 7.2884 7.4103 7.5201 7.6177 7.7039 7.7797 7.8464 7.9051 7.9569 8.2534 8.3771 8.4432 8.4840 8.5116 8.5316 8.5466 8.5584 8.5678

10.1735 10.1736 10.1737 10.1738 10.1739 10.1740 10.1741 10.1742 10.1743 10.1744 10.1745 10.1754 10.1764 10.1774 10.1784 10.1794 10.1803 10.1813 10.1823 10.1833 10.1931 10.2029 10.2127 10.2225 10.2322 10.2419 10.2516 10.2613 10.2710 10.3658 10.4566 10.5423 10.6223 10.6964 10.7646 10.8271 10.8842 10.9363 11.2677 11.4222 11.5081 11.5621 11.5990 11.6258 11.6461 11.6620 11.6747

13.3237 13.3238 13.3238 13.3239 13.3240 13.3241 13.3241 13.3242 13.3243 13.3244 13.3244 13.3252 13.3259 13.3267 13.3274 13.3282 13.3289 13.3297 13.3305 13.3312 13.3387 13.3462 13.3537 13.3612 13.3686 13.3761 13.3835 13.3910 13.3984 13.4719 13.5434 13.6125 13.6786 13.7414 13.8008 13.8566 13.9090 13.9580 14.2983 14.4748 14.5774 14.6433 14.6889 14.7222 14.7475 14.7674 14.7834

16.4706 16.4707 16.4708 16.4708 16.4709 16.4709 16.4710 16.4711 16.4711 16.4712 16.4712 16.4718 16.4725 16.4731 16.4737 16.4743 16.4749 16.4755 16.4761 16.4767 16.4828 16.4888 16.4949 16.5009 16.5070 16.5130 16.5191 16.5251 16.5312 16.5910 16.6498 16.7073 16.7630 16.8168 16.8684 16.9179 16.9650 17.0099 17.3442 17.5348 17.6508 17.7272 17.7807 17.8201 17.8502 17.8739 17.8931

W;'~X*:«";X*~:»»m«*74:*~:::~,»~&::m::m:w:«.::'"X%pt.;.;x.»'W';:,,(";:::;';W4(/'«:xm;:;.»»>.;x-;:~;:~"I);»~&~:x~;g~;*~~x'X«»"&;am>;x::~~*,~y.'l«*;.»x«:*::>>>;::gq;.m.~$$~~,e~-t};~~:x-».

409

410


The obtained (24) satisfies differential equation (1) and boundary conditions (2) and (3) for any i, but does not satisfy the initial condition, since for t = 0 (24) has the form (25) Initial condition (4), T(r,O) = To can be easily satisfied when temperature distribution B(r,t) is the sum of partial solutions of (25) 00

B(r,t) = LAJo(JlnR)e-P/FO

,

(26)

n=1

where Fo = at/r z', Constants A n will be determined from the initial condition. One can multiply both sides of (26) for Fo = 0 by rJo(JimR), and following that integrate them from r = 0 to r = r while accounting for the initial condition (4). As a result, one has

(27)

Next, the integrals [2, 5] are determined

(28)

IrJo[Jln ~ )Jo[JIm ~ )dr =

(29)

2

rz [JimJo (Jin )J1(Jim) - JinJO(Jim )J1(Jin)]

Jim

2

2 -

Jin

Characteristic equation (18) is also satisfied by Jim. By substituting Ji =Jim into (18) and multiplying both sides of (18) by JO(Jin ) , one has (30)

On the other hand, if we substitute Ji = Jin into (18) and multiply both sides of the equation by Jo(Jim)' we have


JlnJO(Jlm)Jl (Jln) = BiJo(Jln )Jo(Jlm) .

411

(31)

From (30) and (31), the equality below follows (32) One can see, therefore, that for m :j:. n the integral (29) equals zero. For m = n, the integral has the form (33) If we account for (28) and (33) in (27), then for m = n we have

2 BOJI (Jln )

(34)


where R = rlrz , Fo = at/r', z When calculating thermal stresses or calculating the amount of energy needed to heat up a cylinder or the energy given off during the cylinder cooling, it is necessary to know what the average temperature of the cylinder is, which is defined as T(t)

1

r

z

z"

= - 2 f 2JrrT(r,t)dr =- 2 frT(r,t)dr. Jrrz

0

rz

(36)

0

Once we account for (37)

and determine T(r,t) from (35), then substitute it into (36) and transform it, we have

412


If we account for the characteristic equation (18), we can write the (38) in the form (39)

A case of an infinitely large heat transfer coefficient a

When heat transfer coefficient a is large, the surface temperature of a cylinder is close to the temperature of a medium. In the case when a ~ 00, then TI r=rz= Tcz • The temperature of the cylinder is formulated in this case as

~_- ~ L...J (}o

!-)

2 J 0 ( lin e-Jl/Fo , n=l linJl (lin) rz

(40)

where lin' n = 1,2 ... are the roots of characteristic equation (22). Average temperature is formulated as

where lin are the roots of Jo(li) = O. Equations (40) and (41) express plate temperature with boundary conditions of 1st kind, when surface temperature of the cylinder undergoes a step increase from initial temperature To at the moment t == 0 to temperature Tcz for time t > o.

Exercise 15.5 A Program for Calculating Temperature Distribution and Its Change Rate in an Infinitely Long Cylinder with Boundary Conditions of 3rd Kind Write a program in FORTRAN language for calculating temperature distribution in an infinitely long cylinder, using the formulas derived in Ex. 15.4. The program should also allow to calculate average temperature and temperature change rate at any point in the cylinder. By means of the developed program, calculate temperature transient on the surface and in the center of the cylinder. Also calculate temperature change rate on the surface and in the center of the cylinder and average temperature transient in time. Assume the following values for the calculation: r = 0.025 m, A = 5 2/s, 50 W/(m·K), a = 1.10- m a = 2000 W/(m 2·K), To = 20 aC, Tcz = 100aC. Apply formulas derived in Ex. 15.4.


413

Solution Temperature change rate is obtained once function T(r,t), formulated in (35), Ex.15.4, is differentiated with respect to time. By accounting that T(r,t) =~r,t)(To - Tc) + I:z ' one gets

dT(r,t) _ 2a(Tcz -To)~ JLn Jl (JLn)Jo(JLn R ) dr

-

2

r,

_Ji2nFo

L..J 2 ( ) 2( ) e. n=l J o JLn + J1 JLn

(1)

A program for calculating temperature distribution T{r,t), average temperature T{t) and temperature change rate dT{r,t)/dt in an infinitely long convectively heated or cooled cylinder

C C C

program for calculating temperature distribution, average temperature and temp. change rate in an infinitely long convectively heated or cooled cylinder program p15_5 dimension eigen(50),zero(100) open(unit=l,file='pI5_5.in') open(unit=2,file='pI5 5.out') read(I,*)ne read(I,*)t_o,t_cz,s_rz,s a read(I,*)s_lam,s alfa read(I,*)nc read (1, *) (zero (i) , i=l, 2*nc, 2) read (1, *) (zero (i) , i=2, 2*nc, 2) write (2, , (a) ') & " CALCULATING CYLINDER TEMPERATURE DISTRIBUTION " write(2,' (/a) ') "INPUT DATA" write(2,' (a,il0) ') "ne =",ne write(2,' (a,el0.5,a) ') "t ° =",t_o," [C]" write(2,' (a,elO.5,a) ') "t cz =",t_cz," [C]" write(2,' (a,el0.5,a) ') "r z =",s_rz," [m]" write(2,' (a,el0.5,a) ') "a =",s_a, " [m"'2/s]" write(2,' (a,el0.5,a) ') "lambda =",s_lam," [W/mK]" write (2, , (a, elO. 5, a) ') "alfa =", s_alfa," [W/m2K]" bi=s - alfa*s - rz/s - lam call equation_roots_cyl(bi,zero,ne,eigen) write(2,' (/a) ')"CALCULATED TEMPERATURE [CJ" write(2,'(a,a)')" t[s] T(O,t) T(r z,t) T_sr(t) & dT/dt(O,t)", dT/dt(r z,t)" t=O. do while (t.le.400.) write (2, , (f5. 0, 5 (3x, el0. 3) ) ') t,

414

15 TransientHeat Conduction in Simple-Shape Elements & & & & &

c

c

c

c c c c

temperature(O.,t,t_cz,t_o,s_rz,s_a,ne,eigen), temperature (s_rz, t,t_cz,t_o,s_rz,s_a,ne,eigen), temperature sr ( t,t_cz,t_o,s_rz,s_a,ne,eigen), temperature_szyb(O., t,t cz,t o,s rz,s a,ne,eigen), temperature szyb(s rz,t,t cz,t o,s rz,s a,ne,eigen) t=t+1. enddo end program p15_5 according to equation (35) in 15.4 function temperature (r,t,t cz,t_o,s rz,s a,ne,eigen) dimension eigen(*) teta=O. do i=l,ne s=eigen(i) teta=teta+bessj1(s)*bessjO(s*rls rz)* &exp(-s**2*s_a*t/s rz**2)/(s*(bessjO(s)**2+ &bessj 1 (s) **2)) enddo temperature=t cz+(t o-t cz)*2.*teta end function according to equation (38) in 15.4 function temperature sr(t,t cz,t o,s rz,s a,ne,eigen) dimension eigen(*) teta=O. do i=l,ne s=eigen(i) teta=teta+bessj1(s)**2* &exp(-s**2*s_a*t/s rz**2)/(s**2*(bessjO(s)**2+ &bessj1(s)**2)) enddo temperature_sr=t cz+(t o-t cz)*4.*teta end function according to equation (1) function temperature szyb(r,t,t cz,t o,s rz,s a,ne, &eigen) dimension eigen(*) teta=O. do i=l,ne s=eigen(i) teta=teta+s*bessj1(s)*bessjO(s*rls rz)* & exp(-s**2*s a*t/s rz**2)/(bessjO(s)**2+bessj1(s)**2) enddo temperature_szyb=2.*s a*(t cz-t o)*teta/s rz**2 end function procedure calculates roots of the characteristic eq. x*J1(x)/JO(x)=Bi where Bi is Biota number, ne number of calculated roots, eigen output vector with calcul. roots, zero() is output vector with function J1(x)

Exercise 15.5 A Program for Calculating Temperature Distribution c

415

and JO(x) zeroing points see Fig.15.II subroutine equation_roots_cyl(bi,zero,ne,eigen) dimension zero(*),eigen(*) pi=3.I4I592654 j=O do i=l,ne xi=zero(i+j) xf=zero(i+l+j) do while (abs(xf-xi) .ge.I.E-05) xm=(xi+xf)/2. y=xm*bessjl (xm)/bessjO (xm)-bi if (y.lt.O.) then xi=xm else xf=xm endif enddo eigen(i)=xm j=j+1 enddo return end

The program does not contain instructions for calculating Bessel functions 10 and 1 1, since they are presented in Ex. 15.4. Temperature calculation results are presented in Fig. 15.12, while the change rate in Fig. 15.13. lOOr---------=::::;;;;;;jiiiiijjjijjiiiiiiii81--~

80

60

40

200 t [s] 250

Fig. 15.12. Outer surface temperature history of a cylinder Ttr , t), center temperature T(O, t) and average temperature T (t) in the function of time

416

15 Transient Heat Conduction in Simple-Shape Elements 3,00....-----------------, dT/dt [K/s] 2,00 r = rz

1,00

0,000

50

100

150

200 t [s] 250

Fig. 15.13. Heating rate history dT(r,t)/dt of an outer surface (r = r) and the center of a cylinder (r = 0) in the function of time

Exercise 15.6 Calculating Temperature in an Infinitely Long Cylinder using the Annexed Diagrams By means of the annexed diagrams [1,2] determine surface temperature in the center line of a steel-made infinitely long cylinder with an outer surface radius r, = 0.05 m (Fig. 15.14). Also calculate the cylinder's average temperature. The surface of the cylinder, which has been heated to the initial temperature of To =100°C, is suddenly cooled by a compressed airflow at the temperature of Tcz = 20°C. Assume the following values for the cal2/s, 5 2·K), A = 50 W/(m·K), a = )Jcp = 1.10- m t= culation: a = 200 W/(m 250 s. Furthermore, determine temperature in the center line of the cylinder, if the heat transfer coefficient is infinitely large, i.e a ~ 00. Also calculate the unknown temperatures by means of the program developed in Ex. 15.5, by accounting for 20 terms in the infinite series.

Solution In order to find the appropriate temperatures in the diagrams given, the Biot and Fourier numbers have to be calculated first

Exercise 15.6 Calculating Temperature in an Infinitely Long Cylinder

417

Bi= arz = 200·0.05 =0.2 A

50

at

1.10-5 • 250

r.

0.05

Fo=z=

' =1.

From the diagram in Fig. 15.15, one has 0100 = 0,66, i.e. T(rz ,t) - Tcz = T(rz ,t) - 20 = 0.66, To - Tcz 100 - 20

hence, follows that T(rz,t) = 72.8°C. From diagram in Fig. 15.16, the dimensionless temperature can be determined in the center line of the cylinder B(O, Fo)/Bo _O(_O,_Fo_) = T(O,t) - 20 = 0.72, 00 100-20

hence, we obtain T(O,t) = 77.6°C.

o

---~

r

Fig. 15.14. The cooling process of a steel cylinder

Average temperature T(t) is read from the diagram in Fig. 15.17

hence, T(t) = (100 - 20)·0.68 + 20 = 74.4°C.

418


When a ~ 00, the dimensionless temperature in the center line of the cylinder cannot be read from the Fig. 15.18. As a result of the calculations conducted by means of the program from Ex.15.5, one has T(rz ,t) = 72.0°C

T(O,t) = 77.3°C T(t) = 74.6°C

and

T( O,t) = 20.4°C Similar results were obtained, with an exception of the case a ~ 00. It is easy to determine temperature when diagrams are used, but such method is less accurate, since not every value of the Biot number has a corresponding curve in the diagrams from Figs. 15.15-15.18.

Appendix 15.2. Diagrams for the calculation of temperature in an infinitely long cylinder with a convective boundary condition SO

40

0

I~O

0,2

0~8

00 °,4

0,6

!

0.6

(t4 l- Q

o.a

0,2

f1

00

1..0 0.,0012

1

0 5 0,01 2

5 0,1 0,2 O~5 I

2

5

10 20

50 100200 5001000

Fo ----....

Fig. 15.15. A change in the dimensionless surface temperature of a cylinder O( 1, = atlrz2, Bi = a

Fo)IOo = [T(rz,t) - TcJ/(To- Tc) in the Fourier number function Fo

rIA z

Exercise 15.6 Calculating Temperature in an Infinitely Long Cylinder

419

O~2 I---+---+---+-+--I++I-J~+-t-+--+l~~--"-++--I-#:----+----..~-+-+ O~8

* I---+--+----I---+-I+-l,........-+l-I--I--+-I-~_+Io__++____I+I-H___++~~__I 0,4

o

I t O~6

0,6 10,4

t

it

80

to LL.-J.~~rtii~.:===~~~::::t=----L---l._L--l---.J

uo:

2

2

5

0 50 100 20() 500 1000

10 20

Fig. 15.16. Temperature changes in the center line of a cylinder B(O,Fo)IBo = [TrO,t) - T~ ]/(To - T~ ) in the Fourier number function F 0 = atlrz2, Bi = a riA \ z

LO

0

0.0012

5 OJ)1 2

5 OJ 0,2 0.5 1 2

5

10 20

50 100 200 500 1000

Fo ---...

Fig. 15.17. Changes in average dimensionless temperature jj/00 T ]/(To - T ) in the Fourier number function F 0 ~

~

= atl r z

2,

Bi = a r z IA

= [T (F0) -

420


0,8

1

06 Fo=08

°

0,2

0,4

0,6

0,8

1,0

R~

Fig. 15.18. Temperature changes in a cylinder elBo = [T(r,t) - Tcz]1 (To - Tcz) in the radial coordinate function R = rlr z with a step change in the cylinder surface temperature from temperature To to temperature Tcz

Exercise 15.7 Formula Derivation for a Temperature Distribution in a Sphere with Boundary Conditions of 3rd Kind Derive a formula for temperature distribution in a sphere with the outer surface radius r, and the convective boundary condition. Initial temperature of the sphere To is uniform. Temperature of the medium increases step-like from the initial temperature ~ to temperature Tcz (Fig. 15.19). Also derive a formula for the average temperature i (t). Consider a specific case, when a~oo.

Solution Temperature distribution is described by the heat conduction equation (1)

Exercise 15.7 Formula Derivation for a Temperature Distribution 421

by boundary conditions

aOI -Aar

=aOI r=rz

aOI

ar r=O

-0

r=~

'

(2)

(3)


(4) where

() = T -

Tez'

()o

= To -

Tez

If a new variable is introduced 9=Or,

(5)

Fig. 15.19. Heating a sphere with a medium, whose temperature undergoes a stepchange from initial temperature To to temperature Tez

422


the initial-boundary problem (1)-(4) can be written as follows:

89

829

8t

8r

-=a2

-:1

89 8r

1 r=~

(6) '

=(a-~J9 r,

(7) r=~

(8)

(9)

Once the separation of variables method is applied, as in the case of the flat wall (Ex. 15.1) the following solution of (6) is obtained that accounts for the boundary condition (8) 2

() = Ae-ak t sin ( k r) .

(10)

By substituting (10) into (7), one obtains - AAk cos (k r, ) = ( a -

k r.

tg ( k r, ) = - - .-

ei-:

~ JA sin (k r, ), (11)

.

If notation f.1 = k r, is introduced, characteristic equation (11) can be written in the form t

-~ gJi- 1- Bi '

(12)

where Bi = a rz /:1. The first six roots of (12) are presented in Table 15.3. Graphical method for determining roots of the characteristic equation (12) is presented in Fig. 15.20. On the basis of this diagram, it is easy to determine the intervals, which contain roots of (12). If (1 - Bi) > 0, then n-th root of (12) lies in the interval

(n-l)JrS;,un

S; Jr

2

+(n-l)Jr, n=l, 2, ..., gdy (l-Bi»O.

(13)

Exercise 15.7FormulaDerivation for a Temperature Distribution 423

Table 15.3. First six roots of the characteristic (12) tgJl = Jl/(1 - Bi) determined by means of the programfor Ex. 15.7 Bi 0.000 0.001 0.002 0.003 0.004 0.005 0.006 0.007 0.008 0.009 0.010 0.020 0.030 0.040 0.050 0.060 0.070 0.080 0.090 0.100 0.200 0.300 0.400 0.500 0.600 0.700 0.800 0.900 1.000 2.000 3.000 4.000 5.000 6.000 7.000 8.000 9.000 10.000 20.000 30.000 40.000 50.000 60.000 70.000 80.000 90.000 100.000

0.0000 0.0548 0.0774 0.0948 0.1095 0.1224 0.1341 0.1448 0.1548 0.1642 0.1730 0.2445 0.2991 0.3450 0.3854 0.4217 0.4551 0.4860 0.5150 0.5423 0.7593 0.9208 1.0528 1.1656 1.2644 1.3525 1.4320 1.5044 1.5708 2.0288 2.2889 2.4556 2.5704 2.6537 2.7165 2.7654 2.8044 2.8363 2.9857 3.0372 3.0632 3.0788 3.0893 3.0967 3.1023 3.1067 3.1102

4.4934 4.4936 4.4939 4.4941 4.4943 4.4945 4.4947 4.4950 4.4952 4.4954 4.4956 4.4979 4.5001 4.5023 4.5045 4.5068 4.5090 4.5112 4.5134 4.5157 4.5379 4.5601 4.5822 4.6042 4.6261 4.6479 4.6696 4.6911 4.7124 4.9132 5.0870 5.2329 5.3540 5.4544 5.5378 5.6078 5.6669 5.7173 5.9783 6.0766 6.1273 6.1582 6.1788 6.1937 6.2048 6.2135 6.2204

7.7253 7.7254 7.7255 7.7256 7.7258 7.7259 7.7260 7.7262 7.7263 7.7264 7.7265 7.7278 7.7291 7.7304 7.7317 7.7330 7.7343 7.7356 7.7369 7.7382 7.7511 7.7641 7.7770 7.7899 7.8028 7.8156 7.8284 7.8412 7.8540 7.9787 8.0962 8.2045 8.3029 8.3913 8.4703 8.5406 8.6031 8.6587 8.9831 9.1201 9.1933 9.2384 9.2690 9.2909 9.3075 9.3204 9.3308

10.9041 10.9042 10.9043 10.9044 10.9045 10.9046 10.9047 10.9048 10.9049 10.9049 10.9050 10.9060 10.9069 10.9078 10.9087 10.9096 10.9105 10.9115 10.9124 10.9133 10.9225 10.9316 10.9408 10.9499 10.9591 10.9682 10.9774 10.9865 10.9956 11.0855 11.1727 11.2560 11.3348 11.4086 11.4773 11.5408 11.5993 11.6532 12.0029 12.1691 12.2618 12.3200 12.3599 12.3887 12.4106 12.4276 12.4414

14.0662 14.0663 14.0663 14.0664 14.0665 14.0666 14.0666 14.0667 14.0668 14.0668 14.0669 14.0676 14.0683 14.0690 14.0697 14.0705 14.0712 14.0719 14.0726 14.0733 14.0804 14.0875 14.0946 14.1017 14.1088 14.1159 14.1230 14.1301 14.1372 14.2074 14.2764 14.3433 14.4080 14.4699 14.5288 14.5846 14.6374 14.6869 15.0384 15.2245 15.3334 15.4034 15.4518 15.4872 15.5140 15.5352 15.5521

17.2208 17.2208 17.2209 17.2209 17.2210 17.2211 17.2211 17.2212 17.2212 17.2213 17.2213 17.2219 17.2225 17.2231 17.2237 17.2242 17.2248 17.2254 17.2260 17.2266 17.2324 17.2382 17.2440 17.2498 17.2556 17.2614 17.2672 17.2730 17.2788 17.3364 17.3932 17.4490 17.5034 17.5562 17.6072 17.6562 17.7032 17.7481 18.0887 18.2869 18.4085 18.4888 18.5450 18.5864 18.6181 18.6431 18.6632

~~"''''''''''''': .. ...- :"""""' . . . W~Q.w@.::t::~::::.w.am."?"~~..«w~;w-..:w~$.o:w&W.:?M&MWZ;.:?~.&:m:¥&.*8WW~z~».:~m::;~ ..:::::::ms:&m:i::::~~

424


When (1 - Bi) < 0, then

;r +(n-l);r::s;,un ::s;;r+(n-l);r, n=l, 2, ..., gdy(l-Bi) 0 by a heat flow at constant density qs (Fig. 15.29). The back surface of the plate (x = L) is thermally insulated. Material properties A-, p, c are constant, while initial temperature To is uniform. Temperature distribution in the plate is expressed by (30), derived in Ex. 15.10. Present the calculation results in a tabular and graphical form.

Solution A program for calculating temperature distribution in an infinite plate heated by a heat flow with density C, = Cis C C C

Calculation of temperature distribution in an infinite plate heated by a heat flow on the front surface and insulated on the back surface program p15_II open(unit=1,file='p15_11.in') open(unit=2,file='p15_11.out') read(l,*)ne write (2, , (a) ') & "CALCULATION OF TEMPERATURE DISTRIBUTION IN A PLATE" write(2,'(/a)') "INPUT DATA" write(2,' (a,ilO) ') "ne =",ne write(2,' (/a) ')"CALCULATED TEMPERATURE [C]" write(2,' (a,a) ')

442

15 Transient Heat Conduction in Simple-Shape Elements &" &

Fo

x/L=O x/L=0,6

x/L=0,2 x/L=0,8

x/L=0,4 x/L=0,5", x/L=l,O"

Fo=O. do while (Fo.lt.0.2) write (2, , (f5. 2,7 (3x, flO. 6)) ') Fo, & temperature_bezw(Fo,O.O,ne), & temperature_bezw(Fo,0.2,ne), & temperature_bezw(Fo,0.4,ne), & temperature_bezw(Fo,0.5,ne), & temperature_bezw(Fo,0.6,ne), & temperature_bezw(Fo,0.8,ne), & temperature_bezw(Fo,1.0,ne) Fo=Fo+.01 enddo do while (Fo.le.1.2) write (2, , (f5. 2,7 (3x, flO. 6)) ') Fo, & temperature_bezw(Fo,O.O,ne), & temperature_bezw(Fo,0.2,ne), & temperature_bezw(Fo,0.4,ne), & temperature_bezw(Fo,0.5,ne), & temperature_bezw(Fo,0.6,ne), & temperature_bezw(Fo,0.8,ne), & temperature_bezw(Fo,1.0,ne) Fo=Fo+.05 enddo end program p15 11 c

according to equation (31) in 15.10 function temperature_bezw(Fo,x_przez L,ne) pi=3.141592654 xpL=x_przez L teta=O. do n=l,ne teta=teta+(-1.)**(n+1)*2.*cos(n*pi*xpL)* &exp(-n**2*pi**2*Fo)/ & n**2/pi**2 enddo temperature_bezw=teta+Fo+0.5*xpL**2-1./6. end function

Plate temperature distribution for selected coordinates x/L is presented in Fig. 15.29 and Table 15.4.

Exercise 15.11 A Program and Calculation Results for Temperature

443

Table 15.4. Dimensionless temperature [T(x,t) - To]/( qs LIA) for the selected values of the dimensionless coordinate X = xlL and the Fourier number Fo = atlL ; the plate is being heated on the front face x = L, while the back surface x = 0 is thermall y insulated 2

Fo 0.00 0.01 0.02 0.03 0.04 0.05 0.06 0.07 0.08 0.09 0.10 0.11 0.12 0.13 0.14 0.15 0.16 0.17 0.18 0.19 0.20 0.25 0.30 0.35 0.40 0.45 0.50 0.55 0.60 0.65 0.70 0.75 0.80 0.85 0.90 0.95 1.00 1.05 1.10 1.15 1.20

0.000000 0.000000 0.000000 0.000005 0.000057 0.000269 0.000786 0.001735 0.003207 0.005251 0.007885 0.011104 0.014887 0.019205 0.024023 0.029306 0.035017 0.041121 0.047584 0.054375 0.061464 0.100516 0.143824 0.189738 0.237244 0.285721 0.334791 0.384223 0.433877 0.483665 0.533536 0.583457 0.633409 0.683380 0.733362 0.783351 0.833344 0.883340 0.933337 0.983336 1.033335

0.000000 0.000000 0.000003 0.000071 0.000393 0.001166 0.002515 0.004489 0.007098 0.010323 0.014132 0.018489 0.023353 0.028684 0.034443 0.040594 0.047102 0.053935 0.061063 0.068460 0.076101 0.117236 0.161821 0.208515 0.256497 0.305265 0.354512 0.404053 0.453773 0.503602 0.553497 0.603433 0.653395 0.703371 0.753356 0.803347 0.853342 0.903339 0.953337 1.003335 1.053334

0.000000 0.000001 0.000153 0.001147 0.003449 0.007040 0.011718 0.017263 0.023492 0.030261 0.037461 0.045011 0.052850 0.060933 0.069223 0.077692 0.086317 0.095079 0.103964 0.112957 0.122047 0.168646 0.216576 0.265313 0.314542 0.364071 0.413784 0.463608 0.513501 0.563436 0.613396 0.663372 0.713357 0.763348 0.813342 0.863339 0.913337 0.963335 1.013335 1.063334 1.113334

0.000000 0.000014 0.000802 0.003722 0.008754 0.015366 0.023074 0.031528 0.040486 0.049784 0.059311 0.068992 0.078777 0.088632 0.098535 0.108469 0.118425 0.128395 0.138375 0.148361 0.158352 0.208336 0.258334 0.308333 0.358333 0.408333 0.458333 0.508333 0.558333 0.608333 0.658333 0.708333 0.758333 0.808333 0.858333 0.908333 0.958333 1.008333 1.058333 1.108333 1.158333

0.000000 0.000000 0.000196 0.010051 0.003396 0.033326 0.010530 0.057196 0.020102 0.079856 0.031010 0.101159 0.042621 0.121223 0.054573 0.140203 0.066658 0.158238 0.078753 0.175447 0.090788 0.191930 0.102722 0.207771 0.114535 0.223039 0.126218 0.237798 0.137770 0.252099 0.149195 0.265989 0.160498 0.279508 0.171687 0.292694 0.182770 0.305578 0.193755 0.318189 0.204650 0.330554 0.258025 0.389430 0.310092 0.444845 0.361354 0.498152 0.412125 0.550170 0.462596 0.601402 0.512883 0.652154 0.563058 0.702614 0.613166 0.752894 0.663231 0.803065 0.713271 0.853170 0.763295 0.903233 0.813310 0.953272 0.863319 1.003296 0.913325 1.053311 0.963328 1.103320 1.013330 1.153325 1.063331 1.203328 1.113332 1.253330 1.163333 1.303331 1.213333 1.353332

0.000203 0.112838 0.159577 0.195441 0.225676 0.252313 0.276395 0.298541 0.319154 0.338514 0.356826 0.374245 0.390892 0.406863 0.422240 0.437089 0.451466 0.465422 0.479000 0.492236 0.505165 0.566146 0.622842 0.676928 0.729423 0.780946 0.831876 0.882444 0.932790 0.983002 1.033131 1.083210 1.133258 1.183287 1.233305 1.283316 1.333323 1.383327 1.433329 1.483331 1.533332

444

15 Transient Heat Conduction in Simple-Shape Elements 1.60 r - - - - - - - - - - - - - - - - . . - - - - . (T - To) A/(4s L)

1.20 x

0.80 0.5 0.4 0.40

0.00

...-.-:::::....--1-._ _1 . - - _ . . - 1 . . -_ _1 . . . - - _ . . - 1 . . - _ - - - - 1

0.00

0.40

0.80

Fo

1.20

Fig. 15.29. Temperature distribution along the thickness of an infinitely long plate heated on the front face (x =L) and thermally insulated on the back surface (x =0)

Exercise 15.12 Formula Derivation for Temperature Distribution in an Infinitely Long Cylinder with Boundary Conditions of 2nd Kind Determine a formula for temperature distribution in an infinitely long cylinder with an outer surface radius r heated by a heat flow at constant density qs (Fig. 15.30). Thermo-physical properties p, A, C are constant. Initial temperature of the plate is uniform and is To' Apply the Laplace transform to solve the initial-boundary problem.

Solution Temperature distribution in the cylinder is governed by the heat conduction equation (1)



445

T

TO~-----ol

r

Fig. 15.30. Diagram that depicts heating of an infinitely long cylinder by a heat flow with constant density qs

aTI =0 ar r=O '

(2)

(3)


(4) Once Laplace transform is applied to (1)-(3) while accounting for the initial condition (4), one has 2

d T 1 dT) a ( dr:- +r-drdT dr

A dT dr where

- o, -sT=T

=0 r=O

(5)

(6) '

(7) r=rz

446

15 Transient Heat Conduction in Simple-Shape Elements t

T=T(x,s)=2'[T(x,t)] = fT(x,t)e-S1dt.

(8)

o

The solution of the boundary problem (5)-(7) is (9)

where q = ~ s/ a . While deriving (9), the following formula for the derivative is used

~ [10 ( qr )] = qIt (qr ) .

(10)

Next, accounting that

10 (qr)

= J o (iqr)

(11)

and

Equation (9) assumes the form

-

To s

. qsJo(iqr) . AqSJl (iqrz )

T--=z

(12)

By substituting Jl = iqrz

(13)

the following characteristic equation is obtained (14) whose roots are Jll = 3.8317; Jl2 =7.0156; Jl3 = 10.1735; Jl4 = 13.3237; Jl5 = 16.4706; Jl6 = 19.6159. The subsequent zeros of the Bessel function lJJl) can be found in tables for special functions, e.g. in [5]. Once functions Io(qr) and IJqr) are expanded into Taylor series, (12) has the form q2 r2

rr

q4 r4

1+--+--+...

.

T-~=~ ( qrz S

4q3 r,364q5r 5 z

sq -+--+--+ ... 2 16 384

hence, after transformations

)'

(15)


'T

sr 2

2·

T-!.!!...= s.« A,rz S2 s

S2

r4

1+-+-2 +...

(1

447

4a 6 4 a . 4 2 z z +sr- + -S2-r2 + ... 8a 192a

(16)

J

A double pole exists in s = 0, while single poles in sn = -f.1n2a/rz2, n = 1,2 ... Temperature distribution is obtained using the inverse Laplace tranformation (Appendix H). From the analysis of (16), it follows that 2· 2 2 · A= 2qsa, B= qsa.!-, D=I, E=!:-. (17)

A,rz

A,rz

4a

8a

Temperature distribution T(r,t) is determined form formula (Appendix H) _ 1 8+ioo_

f

T(r,t)=~-I[T(x,s)J=-. T(r,s)eS1ds= 21(1

_'T

-.IO

A B AE ~ gl(Sn) +-f+--+ L.; e 2

D

Derivative

_ 8 ioo

D

D

n~l

g2(Sn)

(18) Sn t

.

g2 (Sn ) can be calculated from dependence

g2(sn)= dg21

ds s~sn

=~(:tqs)Il(qrz)1 ds

+[:tqSdIl(qrz)] s=sn

ds

(19) S=Sn

By accounting, next, that the first term on the right-hand-side equals zero, due to the fact that the characteristic equation I 1(qnr) = J 1(iqnr) = J 1(lln) = 0, the derivative g2 (Sn ) can be expressed in the following way:

The numerator g/sn) can be transformed in the following way: gl

(Sn ) = 4.'/0 (qn r) =4s J o(iqn r) =4s J o(,un ~ ) ·

By substituting (17), (20) and (21) into (18), one has

(21)

448


(22)

If dimensionless quantities are introduced R =!- i

r,

Fo = at

r,2

(23)

'

temperature distribution T(r,t) can be expressed in the following way:

T(r,t)=To+qSrz[2FO+~R2_~-if J~(,unR) A

2

4

e-IJ;'FO].

(24)

n=l JlnJo (Jln)

For the Fourier number Fo > 0.5, one can neglect the infinite series in (24).

Exercise 15.13 Program and Calculation Results for Temperature Distribution in an Infinitely Long Cylinder with Boundary Conditions of 2nd Kind Write a program for the calculation of temperature distribution in an infinitely long cylinder with an outer surface radius r, heated by a heat flow with constant density qs (Fig. 15.31). Thermo-physical properties A, p, C are constant. Carry out the calculations by means of (24) derived in Ex. 15.12. Present calculation results in a tabular and graphical form

Solution A program for the calculation of temperature distribution in a infinitely long cylinder heated by a heat flow with constant density C C

c's

Calculation of temperature distribution in a long cylinder heated by a heat flow with constant q_s program p15_13 dimension zero(50) open(unit=l,file='pI5_13.in') open(unit=2,file='pI5_13.out') read(l,*)ne read(I,*)nc read (1, *) (zero (i), i=l, nc) write(2,' (a) ')"CALCULATION OF TEMPERATURE IN CYLINDER" write (2, , (fa) ') "INPUT DATA"

Exercise 15.13 Program and Calculation Results 449 =",ne write (2, , (a, i10) ') "ne write(2,' (/a) ')"CALCULATED TEMPERATURE [CJ" write(2,' (a,a) ') r/r_z=0,4 r/r_z=0,2 r/r z=0,5", &" Fo r/r z=O r/r z=0,8 r/r z=l,O" &" r/r z=0,6 Fo=O. do while (Fo.lt.0.2) write (2, , (f5. 2,7 (3x, flO. 5) ) ') Fo, temperature_bezw_cyl(zero,Fo,O.O,ne), & temperature_bezw_cyl(zero,Fo,0.2,ne), & temperature_bezw_cyl(zero,Fo,0.4,ne), & temperature_bezw_cyl(zero,Fo,0.5,ne), & temperature_bezw_cyl(zero,Fo,0.6,ne), & temperature_bezw_cyl(zero,Fo,0.8,ne), & temperature_bezw_cyl(zero,Fo,1.0,ne) & Fo=Fo+.01 enddo do while (Fo.le.1.2) write (2, , (f5. 2,7 (3x, flO. 5)) ') Fo, temperature_bezw_cyl(zero,Fo,O.O,ne), & temperature_bezw_cyl(zero,Fo,0.2,ne), & temperature_bezw_cyl(zero,Fo,0.4,ne), & temperature_bezw_cyl(zero,Fo,0.5,ne), & temperature_bezw_cyl(zero,Fo,0.6,ne), & temperature_bezw_cyl(zero,Fo,0.8,ne), & temperature_bezw_cyl(zero,Fo,1.0,ne) & Fo=Fo+.05 enddo end program p15_13 c according to equation (24) in 15.12 R=r/r_z, Fo=at/r z/r z function temperature_bezw_cyl(zero,Fo,R,ne) dimension zero(*) pi=3.141592654 teta=O. do n=l,ne s=zero(n) teta=teta+bessjO(s*R)*exp(-s**2*Fo)/( s**2*bessjO(s) enddo temperature_bezw_cyl=-2.*teta+2.*Fo+0.5*R**2-1./4. end function FUNCTION bessjO(x) REAL bessjO,x REAL ax,xx,z DOUBLE PRECISION p1,p2,p3,p4,p5,q1,q2,q3,q4,q5, & r1,r2,r3,r4,r5,r6,sl,s2,s3,s4,s5,s6,y SAVE p1,p2,p3,p4,p5,q1,q2,q3,q4,q5,r1,r2, & r3,r4,r5,r6,sl,s2,s3,s4,s5,s6

450

15 Transient Heat Conduction in Simple-Shape Elements DATA pl,p2,p3,p4,p5/1.dO,-.1098628627d-2, .2734510407d&4,-.2073370639d-5, .2093887211d-6/, ql,q2,q3,q4,q5/ &-.1562499995d-l, .1430488765d-3,-.6911147651d-5, &.7621095161d-6,-.934945152d-7/ DATA rl,r2,r3,r4,r5,r6/57568490574.dO,-13362590354.dO, &651619640.7dO,-11214424.18dO,77392.33017dO, &-184.9052456dO/,sl,s2,s3,s4,s5,s6/57568490411.dO, &1029532985.dO,9494680.718dO,59272.64853dO, &267.8532712dO,1.dO/ if(abs(x) .It.8.)then y=x**2 bessjO=(rl+y*(r2+y*(r3+y*(r4+y*(r5+y*r6)))))/ &(sl+y*(s2+y*(s3+y*(s4+y*(s5+y*s6))))) else ax=abs(x) z=8./ax y=z**2 xx=ax-.785398164 bessjO=sqrt(.636619772/ax)*(cos(xx)* &(pl+y*(p2+y*(p3+y* &(p4+y*p5))))-z*sin(xx)*(ql+y*(q2+y*(q3+y*(q4+y*q5))))) endif return END

Dimensionless temperature distribution for selected dimensionless coordinates rlr, is presented in Fig. 15.31 and Table 15.5. 3,00r----------------..., T

(T - To) AI(qs rz) .

~

2,00

0,5 1,00

0,4 0,2

0,40

0,80 Fo = atlr} 1,20

Fig. 15.31. Temperature transient in an infinitely long cylinder heated by a constant density heat flow

Exercise 15.13 Program and Calculation Results 451

Table 15.5. Dimensionless temperature in an infinitely long cylinder [T(r,t) To]/ ( qs L/ A) for the selected values of the dimensionless coordinate R = r/ r, and the Fourier number Fo = atlr'z Fo 0.00 0.01 0.02 0.03 0.04 0.05 0.06 0.07 0.08 0.09 0.10 0.11 0.12 0.13 0.14 0.15 0.16 0.17 0.18 0.19 0.20 0.25 0.30 0.35 0.40 0.45 0.50 0.55 0.60 0.65 0.70 0.75 0.80 0.85 0.90 0.95 1.00 1.05 1.10 1.15 1.20

0.00256 0.00000 0.00000 0.00003 0.00028 0.00120 0.00325 0.00676 0.01188 0.01862 0.02692 0.03667 0.04771 0.05993 0.07317 0.08731 0.10223 0.11784 0.13405 0.15077 0.16794 0.25861 0.35413 0.45198 0.55095 0.65046 0.75022 0.85011 0.95005 1.05002 1.15001 1.25001 1.35000 1.45000 1.55000 1.65000 1.75000 1.85000 1.95000 2.05000 2.15000 ......

.

=0.2

=0.4

0.00036 0.00000 0.00001 0.00017 0.00096 0.00291 0.00636 0.01147 0.01822 0.02655 0.03632 0.04741 0.05965 0.07293 0.08710 0.10205 0.11769 0.13391 0.15065 0.16784 0.18540 0.27739 0.37355 0.47170 0.57082 0.67039 0.77019 0.87009 0.97004 1.07002 1.17001 1.27000 1.37000 1.47000 1.57000 1.67000 1.77000 1.87000 1.97000 2.07000 2.17000

0.00024 0.00000 0.00025 0.00192 0.00585 0.01211 0.02044 0.03052 0.04206 0.05483 0.06863 0.08331 0.09873 0.11479 0.13140 0.14847 0.16594 0.18376 0.20188 0.22026 0.23886 0.33425 0.43204 0.53098 0.63047 0.73023 0.83011 0.93005 1.03003 1.13001 1.23001 1.33000 1.43000 1.53000 1.63000 1.73000 1.83000 1.93000 2.03000 2.13000 2.23000

= 1.0 0.00022 0.00002 0.00118 0.00556 0.01326 0.02359 0.03588 0.04963 0.06449 0.08021 0.09661 0.11357 0.13097 0.14876 0.16686 0.18523 0.20382 0.22261 0.24157 0.26067 0.27989 0.37735 0.47613 0.57554 0.67526 0.77512 0.87506 0.97503 1.07501 1.17501 1.27500 1.37500 1.47500 1.57500 1.67500 1.77500 1.87500 1.97500 2.07500 2.17500 2.27500 ..

...

0.00021 0.00026 0.00457 0.01439 0.02785 0.04351 0.06054 0.07842 0.09685 0.11567 0.13474 0.15400 0.17339 0.19290 0.21248 0.23213 0.25183 0.27157 0.29136 0.31117 0.33101 0.43048 0.53023 0.63011 0.73005 0.83003 0.93001 1.03001 1.13000 1.23000 1.33000 1.43000 1.53000 1.63000 1.73000 1.83000 1.93000 2.03000 2.13000 2.23000 2.33000 =.. "." ..

m:.-::mm:~ .;.~~~~-?~~~~~~~~.~~.&33~~ :

0.00027 0.01159 0.03918 0.06830 0.09669 0.12402 0.15036 0.17582 0.20051 0.22456 0.24805 0.27105 0.29364 0.31588 0.33781 0.35948 0.38091 0.40215 0.42323 0.44415 0.46495 0.56758 0.66884 0.76944 0.86973 0.96987 1.06994 1.16997 1.26999 1.36999 1.47000 1.57000 1.67000 1.77000 1.87000 1.97000 2.07000 2.17000 2.27000 2.37000 2.47000 = .:._ . .•

~.~:8)~~.&.v.«&.~=

0.01026 0.11814 0.17046 0.21210 0.24829 0.28104 0.31139 0.33995 0.36712 0.39317 0.41833 0.44273 0.46650 0.48973 0.51252 0.53492 0.55698 0.57876 0.60030 0.62163 0.64277 0.74653 0.84834 0.94920 1.04962 1.14982 1.24991 1.34996 1.44998 1.54999 1.65000 1.75000 1.85000 1.95000 2.05000 2.15000 2.25000 2.35000 2.45000 2.55000 2.65000

= . ~ ~

452


Exercise 15.14 Formula Derivation for Temperature Distribution in a Sphere with Boundary Conditions of 2nd Kind Determine a formula for temperature distribution in a sphere with an outer surface radius r heated by a heat flow with constant density qs (Fig. 15.32). Thermo-physical properties p, A, c are constant. Initial temperature of the sphere is uniform and measures To' Apply Laplace transform to solve the initial-boundary problem.

T~

! I

1(1',/)

I r

..

Fig. 15.32. The sphere heating by a heat flow with constant density

qs

Solution Temperature distribution in a sphere is governed by the heat conduction equation (1)


aTI =0 ar r=O ' IJ /l"

aTI 8r

-' -qs r=rz

(2)

(3)

Exercise 15.14 Formula Derivation for Temperature Distribution in a Sphere

453

and by initial-boundary condition

(4)

Tlt=o = To.

Once Laplace transform is applied to (1)-(3), while accounting for initial condition (4), one has 2

d T 2 dTJ a ( dr:- +r-dr- -sT=To, dT dr

(5)

(6)

=0 r=O

'

)., dT dr

r=rz

(7)

s

where 00

T =T(r,s) = 2'[T(r,t)] = fT(r,t )e-st dt.

(8)

o

Solution of the boundary problem (5)-(7) has the form

- To sinh ( qr) cosh ( qr) T=-+A +B , s

r

r

(9)

where q=~s/a. Due to the finite temperature value inside the sphere r = 0 constant B equals zero. Constant A determined from condition (7) has the form

.21

A=~~

AS qrz cosh ( qr. ) - sinh ( ar. )

.

(10)

By substituting A into (9), while noting that B = 0, a formula for a temperature distribution in the image domain is obtained

Function (11) has a single pole in s =0 and single poles, which constitute the roots of the following transcendental equation

g2(S)=0,

(12)

hence, qrz cosh (qrz ) - sinh (qrz )

=0 .

(13)

454


By substituting u

= iqrz into (13), one has

~ COSh(~)-Sinh(~ )=0,

(14)

~ cosh(-ill) - sinh( -ill) = 0, 1

hence, by accounting that coshj -(u) = cOSJl

oraz

sinh ( -iJl) = -isinJl

(15)

one obtains Jl cos Jl- sin Jl = 0,

(16) tgjz

= u.

If we assume that

lin = iqnrz,

(17)

then 2

s;

u;«

(18)

=--2 .

r.

The roots of the characteristic equation (16) (the first five) are =4.4934; 112 =7.7253; 11 3 = 10.9041; 114 = 14.4934 and 115 = 17.2208. Once the functions, sinh(qr), cosh(qr) and sinh(qr) in the (11) are expanded into the Taylor series (see Appendix H), one has

III

•

J

2

(

q3r3 qr+(1+S1+...) 6-+···

~(s)e~=qs~ ~~~~~~~~~~~~~~~~~~

Ar s[qrz(1+

q2;}

+q~4 +...J_(qrz+ q3;z3 +~5;~ +..J]

(19)

sr2 . (1+ +...J(1+S1+ ...) _ qsrz 6a - A

s2(r} + sr}2 ...J 3a

30a

From the analysis of this expression it follows that (see Appendix H)

A= qsrz A '

· 2 2

B= qsrz !..A 6a'

D=!!3a '

4

E=~ 30a 2 •

(20)

By accounting for formula (H.25) from Appendix H, one obtains (k = 2)

Exercise 15.14 Formula Derivation for Temperature Distribution in a Sphere

C-l

=

~ ( At + B - ~ J= q~z ( ~; t + ~ ~z: - 1~ ) ·

455

(21)

Temperature distribution T(r,t) is determined from formula (see Appendix H) _ 1 O+ioo_

T(r,t) =2:-1[T(r,s)] = - . 2JrI _T 1 -10+-

f T(r,s)e~stds=

o_ioo

(22)

(A t+ B-AEJ ~ gl(Sn) e. - +L..J snt

D

n=l g2(Sn)

D

For a single pole s the form

=0 ((H.8) in Appendix H), the derivative

g2 (Sn) = Arsnh'(Sn) = Arsn~[qrz cosh ( qrz) -

g2(sn)has

sinh ( qrz) JI

ds

S=Sn

q ds

=Arsn {d rz cosh ( qrz ) + qrz sinh ( qrz ) dq rz ds

-cosh( qrz ) dq rz} ds

(23)

= Arrz q~ sinh ( qnrz ) = 2

S=Sn

1 j.l; SIn . h ( -1-. j.ln J=- 2"1 Ar 1 · h( . ) 1. 1 2 · =Ar 2i u;2SIn -1 u; = 2"IAr u; SIn j.ln. 2

When determining g2(s n ) , the following is accounted for

dq q s-=-. ds 2 Next, numerator is determined 2

(24)

2

gl (Sn ) = 4s rz sinh ( qnr) = 4s rz sinh

h(·-lJln rz J -lqsrz ..

• 2 sm . = qsrz

r

=

2

(~n rJ = Ir z

. ( sm

(25)

J

u; rr · z

By substituting dependencies (21), (23) and (25) into (22), one has

. (

2 ) . srz2

T(r,t) = 1'0 +qsrz 3~t +!;--~ 2 r, 10 A r,

_2q

I

00

. ( u; -r SIn 2.

rz

Ar n=l u; SInu;

J

2

at

/n ri.

(26)

Assuming that the dimensionless radius is R = (rlr) and the Fourier number is F0 = atlrz2, (26) can be written in the form

456


[T(r,t)-ro Jt qsrz

1

-=----~=3Fo+-R

2

2

3 ~ sin(,unR) ---2LJ 10 n=l u.R

e-f-/;;Fo

u; sin f.Jn

.

(27)

For Fo > 0.5 one can neglect the infinite series in the above formula.

Exercise 15.15 Program and Calculation Results for Temperature Distribution in a Sphere with Boundary Conditions of 2nd Kind Write a program for the calculation of temperature distribution in an infinitely long cylinder with the outer surface radius r z heated by a heat flow with constant density qs (Fig. 15.33). Thermo-physical properties A, p, C are constant. Carry out the calculations using (26) derived in Ex. 15.14. Present the calculation results in a tabular and graphical form.

Solution Program for calculating temperature distribution in a sphere heated by a heat flow with constant heat flux C C

its

Calculation of temperature distribution in a sphere heated by a heat flow with constant heat flux q_s program p1S_1S dimension eigen(SO) open(unit=1,file='p1S lS.in') open(unit=2,file='p15_15.out') read(l,*)ne write(2,' (a) ') & "CALCULATION OF TEMPERATURE DISTRIBUTION IN SPHERE" write (2, , (/a) ') "INPUT DATA" write(2,' (a,ilO) ') "ne =",ne call equation_roots_sph(O.O,ne+l,eigen) write (*, *) (eigen (i), i=l, 6) write(2,' (/a) ')"CALCULATED TEMPERATURE [C]" write(2,' (a,a) ') &" Fo r/r_z=O,O r/r_z=0,2 r/r_z=0,4 &"r/r_z=0,5", r/r_z=0,6 r/r z=0,8 r/r_z=l,O" Fo=O. do while (Fo.lt.0.2) write (2, , (f5. 2,7 (3x, flO. 5)) ') Fo, & temperature_bezw_sph(eigen,Fo,O.,ne), & temperature_bezw_sph(eigen,Fo,0.2,ne), & temperature_bezw_sph(eigen,Fo,0.4,ne), & temperature_bezw_sph(eigen,Fo,0.5,ne),

Exercise 15.15 Program and Calculation Results forTemperature

c

c c c

457

& temperature_bezw_sph(eigen,Fo,O.6,ne), & temperature_bezw_sph(eigen,Fo,O.8,ne), & temperature_bezw_sph(eigen,Fo,1.0,ne) Fo=Fo+.Ol enddo do while (Fo.le.l.2) write(2,' (f5.2,7(3x,fl0.5)) ')Fo, & temperature_bezw_sph(eigen,Fo,O.,ne), & temperature_bezw_sph(eigen,Fo,O.2,ne), & temperature_bezw_sph(eigen,Fo,O.4,ne), & temperature_bezw_sph(eigen,Fo,O.5,ne), & temperature_bezw_sph(eigen,Fo,O.6,ne), & temperature_bezw_sph(eigen,Fo,O.8,ne), & temperature_bezw sph(eigen,Fo,1.0,ne) Fo=Fo+.05 enddo end program p15 15 according to Eq. (27) in 15.14, R=r/r_z, Fo=at/r z/r z function temperature_bezw_sph(eigen,Fo,R,ne) dimension eigen(*) pi=3.141592654 teta=O. do n=l,ne s=eigen(n+l) if (R.eq.O.) then teta=teta+exp(-s**2*Fo)/(s*sin(s)) else teta=teta+sin(s*R)*exp(-s**2*Fo)/(s*R*s*sin(s)) endif enddo temperature bezw sph=-2.*teta+3.*Fo+O.5*R**2-3./10. end function procedure calculates roots of the ch. eq. x*cot(x)=l-Bi where Bi is Biot number, ne is number of calculated roots, eigen is output vector with calculated roots subroutine equation roots sph(bi,ne,eigen) dimension eigen(*) pi=3.141592654 if ((bi.eq.l.) .or. (bi.gt.l0000.)) then do i=l,ne if(bi.eq.l.) eigen(i)=(2.*float(i)-1.)*pi/2. if(bi.gt.l0000.) eigen(i)=float(i)*pi enddo else h=l.-bi if (h.lt.O.) then hl=pi/2.

458

15 Transient Heat Conduction in Simple-Shape Elements h2=pi else hl=O. h2=pi/2. endif do i=l,ne xi=hl+(float(i)-l.)*pi xf=h2+(float(i)-1.)*pi do while (abs(xf-xi) .ge.5.E-06) xm=(xi+xf)/2. y=xm*cos(xm)/sin(xm)-h if (y.lt.O.) then xf=xm else xi=xm endif enddo eigen(i)=xm enddo endif return end

Dimensionless temperature distribution for the selected coordinates rlr is presented in Fig. 15.33 and Table 15.6. Table 15.6. Dimensionless temperature in a sphere [T(r,t) - ToJ/( qs L/.,1,) for the selected values of the dimensionless coordinate R=r/rz and the Fourier number Fa =atlr z' Fo 0.00 -0.02891 0.01 0.00000 0.02 0.00000 0.03 0.00009 0.04 0.00088 0.05 0.00342 0.06 0.00865 0.07 0.01699 0.08 0.02848 0.09 0.04288 0.10 0.05988 0.11 0.07911 0.12 0.10023 0.13 0.12293 0.14 0.14694 0.15 0.17203 0.16 0.19801

=0.4 -0.00266 0.00000 0.00001 0.00038 0.00211 0.00631 0.01358 0.02404 0.03753 0.05373 0.07229 0.09284 0.11507 0.13870 0.16347 0.18919 0.21569

-0.00248 0.00000 0.00040 0.00310 0.00950 0.01976 0.03346 0.05008 0.06912 0.09015 0.11281 0.13682 0.16192 0.18791 0.21464 0.24196 0.26977

=0.8 0.00003 0.00170 0.00811 0.01948 0.03489 0.05337 0.07421 0.09686 0.12093 0.14614 0.17224 0.19907 0.22649 0.25439 0.28267 0.31126

-0.00213 0.00034 0.00607 0.01931 0.03772 0.05942 0.08327 0.10860 0.13497 0.16210 0.18982 0.21799 0.24651 0.27530 0.30433 0.33353 0.36289

-0.00124 0.01331 0.04575 0.08084 0.11576 0.15002 0.18360 0.21656 0.24900 0.28100 0.31264 0.34398 0.37508 0.40598 0.43671 0.46731 0.49780

0.12364 0.18192 0.22985 0.27260 0.31217 0.34956 0.38538 0.42002 0.45375 0.48676 0.51920 0.55119 0.58281 0.61413 0.64520 0.67608

Exercise 15.15 Program and Calculation Results for Temperature

459

Table 15.6. (cont.) Fo 0.17 0.18 0.19 0.20 0.25 0.30 0.35 0.40 0.45 0.50 0.55 0.60 0.65 0.70 0.75 0.80 0.85 0.90 0.95 1.00 1.05 1.10 1.15 1.20

=0

=0.2

=0.4

=0.5

0.22472 0.25203 0.27983 0.30804 0.45293 0.60107 0.75039 0.90014 1.05005 1.20002 1.35001 1.50000 1.65000 1.80000 1.95000 2.10000 2.25000 2.40000 2.55000 2.70000 2.85000 3.00000 3.15000 3.30000

0.24282 0.27048 0.29856 0.32700 0.47255 0.62093 0.77034 0.92012 1.07005 1.22002 1.37001 1.52000 1.67000 1.82000 1.97000 2.12000 2.27000 2.42000 2.57000 2.72000 2.87000 3.02000 3.17000 3.32000

0.29799 0.32653 0.35533 0.38436 0.53159 0.68058 0.83021 0.98008 1.13003 1.28001 1.43000 1.58000 1.73000 1.88000 2.03000 2.18000 2.33000 2.48000 2.63000 2.78000 2.93000 3.08000 3.23000 3.38000

0.34012 0.36918 0.39842 0.42779 0.57602 0.72537 0.87514 1.02505 1.17502 1.32501 1.47500 1.62500 1.77500 1.92500 2.07500 2.22500 2.37500 2.52500 2.67500 2.82500 2.97500 3.12500 3.27500 3.42500

4.00

0.39236 0.42193 0.45157 0.48129 0.63047 0.78017 0.93006 1.08002 1.23001 1.38000 1.53000 1.68000 1.83000 1.98000 2.13000 2.28000 2.43000 2.58000 2.73000 2.88000 3.03000 3.18000 3.33000 3.48000

aJ

~

r 1 (T- 'o ))'J(4s z) -.' _

.

,~~~,

Pi

= 1.0 0.70680 0.73738 0.76786 0.79825 0.94936 1.09977 1.24992 1.39997 1.54999 1.70000 1.85000 2.00000 2.15000 2.30000 2.45000 2.60000 2.75000 2.90000 3.05000 3.20000 3.35000 3.50000 3.65000 3.80000

m

.' qs

I

3.00

=0.8 0.52821 0.55853 0.58880 0.61902 0.76964 0.91987 1.06995 1.21998 1.36999 1.52000 1.67000 1.82000 1.97000 2.12000 2.27000 2.42000 2.57000 2.72000 2.87000 3.02000 3.17000 3.32000 3.47000 3.62000

~

0.5 0.6

0.8 2.00 0.4

1.00

0.2

o. 00 -~....I--_---'-_----I'---_-'--_---'-_----J 0.00

0.40

O.80 F,o = atlr] 1.20

Fig. 15.33. Temperature transient of a sphere heated by a heat flow with constant density

qs

460


Exercise 15.16 Heating Rate Calculations for a Thick-Walled Plate Steel plate, 2L = 300 mm thick is heated in a furnace, whose chamber temperature is Tcz = 850°C. Temperature of the plate, before it is placed in the furnace is constant and is To = 20°C. Heat transfer coefficient on the plate 2·K). Due to a considerable surface is constant and equals a = 250 W/(m width and length of the plate with respect to its thickness, assume that the plate is infinite, i.e. that the temperature distribution in the plate is onedimensional. Calculate the amount of heat (energy) accumulated by 1 m' of the plate during 1 hour from the moment the plate is placed in the furnace. Also calculate the temperature in the center and on the plate surface. Thermal conductivity of the steel is .It. = 36 W/(m·K), while temperature 6 2/s. diffusivity coefficient a = 9.10- m

Solution The amount of energy transferred by 1 m' of the plate can be calculated from formula M

= £2 -

£1

J

J

= PAC[ T(X,h)dx- T(X,t1)dx] =

~

l

(1)

=PAC[ 2!T(X,t2)dx - u.i; ] = PAC[2L !T (x, t: )dx- 2LTo M=2LpAc[f(t2)-ToJ'

(2)

where A = 1 m' is the surface area of the heated plate (from one side only), pc = Ala = 36/(9.10-6 ) = 4.10 6 J/(m3·K). Carry out the calculations by means of the program developed in Ex. 15.2. Average temperature T(/2) is calculated as follows _ 1L ~c (/)1 t2=3600s =-L JT( X,/2 )dx = 577°C. o Plate surface temperature is T(L,12) = 650°C, while temperature of the plate center is T(0,12) = 539°C. The energy amount is determined from (2) M=2.1.4.10 6(577-20)= 4,456·10 9J. Calculations can also be done using the diagrams shown in Ex.15.3. Fourier Fo and Biot numbers are

Exercise 15.17 Calculating the Heating Rate of a Steel Furnace Shaft 6

Fo = al2 = 9.10- • 3600 = 1.44 L2 0.152

Bi

461

= aL = 250· 0.15 = 1.042. A

36

Average temperature 1fleo taken from the diagram in Fig. 15.8 is

1f

eo

=

Tcz - T (12) ~ 0.33 Tcz - To

hence,

T (12) = Tcz - 0.33(Tcz - To) = 850 -

0.33(850 - 20) = 576.1°C.

Plate surface temperature is (diagram, Fig. 15.6)

e( L,(2) Tcz - T(L,12) = ~ 0.24 , eo Tcz - To

--:..-~

hence,

T(L,12) = Tcz - 0.24(Tcz - To) = 850- 0.24(850- 20) = 650.8°C. Temperature of the plate center taken from the diagram in Fig. 15.7 is

e (0,12 ) t; - T(0,12 ) ~0.37, eo Tcz - To

~~=

hence,

T(0,(2) = Tcz - 0.4(Tcz - To) = 850- 0.4(850 - 20) = 518°C. The amount of energy accumulated by the plate, and calculated on the basis of temperatures taken from the diagrams, is fill

= 2.1.4.106 (576.1-20) = 4.45 .10 9 J.

Calculation results obtained by means of the program are more accurate.

Exercise 15.17 Calculating the Heating Rate

of a Steel Shaft Long steel shaft with a diameter that is d = 2rz = 120 mm was placed in a furnace with a temperature of 800°C. How long should a shaft with an initial temperature of To = 20 0 e be heated so that temperature would reach T(O,tn ) = 644°e at the shaft axis? Also determine surface temperature of the shaft at the end of the heating process, i.e. the temperature T(rz,tn ) . Use the following data for the calculation: thermal conductivity A = 21

462

15 Transient Heat Conduction in Simple-Shape Elements 6

2/s,

W/(m·K), temperature diffusivity a = 6.10- m heat transfer coefficient 2·K). Carry out the calculations by on the shaft surface a = 140 W/(m means of the program presented in Ex. 15.5 and by using the diagrams from Ex. 15.6.

Solution Once the calculations are completed by means of the program developed in Ex.15.5, the following results are obtained: • time tn = 1405.31 s, • shaft surface temperature after time tn: T(rz,tn) = 671.02°C. In order to make use of the diagrams presented in Ex. 15.6, calculate dimensionless temperature B/Bo and the Biot number Bi first

B T( O,tn)- Tcz 644 - 800 -02 Bo - To - Tcz - 20 - 800 - . ,

--

Bi= arz = 140·0.06 =0.4. A 21

From Fig. 15.16, Ex. 15.6, one has

Fo= a~ =2.4 r, hence 2

_ Fo r; -_ 2.4.0.06 -1440 . s -- 24 mIn. a 6.10-6

t, -

Dimensionless temperature of the surface B/Bo for Fo = 2,4 taken from the diagram in Fig. 15.15, Ex. 15.6 is

B T(rz,tn)-Tcz Bo To - Tcz

-=

~0.15,

hence

T(rz,t n) = 0.15( 20 - 800) + 800 = 683°C. Results obtained by means of the computational program are more accurate than the results determined by means of the diagrams.

Exercise 15.18 Determining Transients of Thermal Stresses 463

Exercise 15.18 Determining Transients of Thermal Stresses in a Cylinder and a Sphere Determine transients of thermal stresses in the centre line of an infinitely long cylinder and inside a sphere. In both cases, assume the following data 2/s, 6 a = 200 for the calculation: r z = 0.025 m, A = 40 W/(m·K), a = 8.10- m 2·K), W/(m f/J w = EfJI(I-v) = 3.7 MPalK, Tcz = 20°C, To = 750°C. In order to determine stresses, apply computational programs developed in Ex. 15.5 and 15.8.

Solution Thermal stresses are calculated from formula [6] {JT

= fPw [ t; (t ) -

while the material constant

(jjw

(1)

T ( r, t ) ] '

is given by

fPw= Efi ,

(2)

I-v where E [MPa] is the longitudinal elasticity module, mal expansion coefficient, v a Poisson ratio.

f3 [11K]

a linear ther-

80,..----------------. aT[MPa] , \

, ""

40

r=r..

,

--cylinder - - - - - sphere

" ....

o -40

1'=0 'I

I

-80

I

I

I

l'

o

800 t [sOl 1000

Fig. 15.34. Thermal stresses transient in a cylinder and a sphere caused by a sudden drop in temperature (cooling)

464


Average temperature is defined as (3)

where: m = 1 for a cylinder and m = 2 for a sphere. Calculation results are presented in Fig.15.34. One can conclude from them that thermal stresses are extensible on the surface, while compressible in the centre line of the cylinder and inside the sphere. Maximum compressible or extensible stresses occur at the beginning of the cooling process. Despite the large difference in temperature between initial temperature To = 750°C and medium's temperature Tez = 20°C, the absolute stress value is not very high, since the heat transfer coefficient is relatively small.

Exercise 15.19 Calculating Temperature and Temperature Change Rate in a Sphere Calculate temperature and temperature change rate inside a sphere with a radius of r = 30 mm in time t = 10 s. Initial temperature of the copper sphere is To = 30°C. The sphere surface is tarnished black and its emissivity G is of 0.97. The sphere was suddenly placed in a furnace chamber of a power boiler, whose temperature was T, = 1350°C. Assume the following thermo-physical properties of copper for the calculation: A = 386 W/(m·K), 5 2/s. a = 11.23.10- m

Solution First calculate heat flux on the sphere surface

qs = EO" [ Tk4 8

T

4

(rz ,t ) ]

'

(1)

2·K4

where a = 5.67.10- W/(m ) is the Stefan-Boltzmann constant. Taking into account that at an initial heating stage T, >>Ttr, t), (1) is simplified to a form

r

qs = EO"Tk4 = 0.97· 5.67 .10-8 • (1350 + 273 = 381618 W/m 2 • Assuming that 5

D

ro

==

at == 11.23.10- ·10 == 4 99 2 2· »0.5, r; 0.015

(2)

Exercise 15.20 Calculating Sensor Thickness for Heat Flux Measuring

465

Equation (26) in Ex. 15.14 for the calculation of sphere temperature can be simplified to a form

1 r- - 3J T( rt -+) =To +-qs r, (3at 2

,

r}

A

2 r}

10'

(3)

where from it is easy to determine temperature change rate dT

qsrz

3a

dt

A

rz

(4)

vr=-=-'-2 .

Temperature inside the sphere after time t = 10 s from the moment the sphere is placed inside the furnace, calculated from (3) is 1;;

=T(O

10 8)=30+ 381618.0.015(3.11.23.10- ·10 -~J=247.6°C. , 386 0.0152 10 5

Temperature change rate inside the sphere is 5

VT

= 381618· 0.015 3 ·11.23 .10- = 22.2 K . 386 0.015 2 s

Exercise 15.20 Calculating Sensor Thickness for Heat Flux Measuring A flat sensor (a slug calorimeter), insulated on the back and lateral surfaces (Fig. 15.35) was used for measuring heat flux qs absorbed by a furnace chamber water-wall of a boiler (thermal load). Maximum value qs does 2 not exceed 400 000 W/m • Due to the accuracy of the measurement, the temperature change rate vT measured on the sensor's back surface should not be very high. Assume that the sensor is made of a chrome-nickel steel (20% Cr, 15% Ni) and calculate the thickness of the sensor L, so that the rate of temperature increase would be vT :S 5 K/s. Assume the following 2/s. steel properties for the calculation: A =15.1 W/(m·K), a = 4.2.10-6 m

Solution Measurements are taken during a quasi-steady state, when the following condition is satisfied at

FO=-2

L

>0.5,

(1)

466


hence, follows that 0.5L2

(2)

t~--.

a

During the quasi-steady state, temperature distribution in the sensor is given by (32) from Ex. 15.10 1] +"21 ( LX)2 -6"'

qsL [ at T (x,t) =To+T L2

(3)

Temperature change rate vr is

dT

qsL a

dt

A L

(4)

VT=-=--· 2

x

thermal insulation

'\

thennoelement sensor

Fig. 15.35. Diagram of a sensor used for measuring thermal loads in furnace chamber water-walls of a boiler

From condition VT

S Vmax ,

q.L a < max -z-v A L one obtains

(5)

Literature

L2~, AVmax

467

(6)

6

L? 400000· 4.2 .10- = 0.02225 m.

15.1·5 From condition (2) it follows that the measurement vT should be taken for time 2

2

> 0.5L = 0.5· 0.02225 = 58 9

t-

a

6'

4.2·10-

s,

i.e. after t 2: about 1 min after the probe is placed inside the furnace.

Literature 1. Gerald CF, Wheatley PO (1994) Applied Numerical Analysis. Reading. Addison-Wesley 2. Carslaw HS, Jaeger JC (1959) Conduction of Heat in Solids. Clarendon Press. Oxford 3. Grober G, Erk S, Grigull U (1960) Warmeubertragung, Teubner, Stuttgart 4. IMSL (International Mathematical and Statistical Library). Inc. Houston TX(713): 242-6776 5. Jahnke E, Emde F, Losch F (1960) Tafeln hoherer Funktionen. Teubner, Stuttgart 6. Noda N, Hetnarski RB, Tanigawa Y (2000) Thermal Stresses. Lastran Corporation, Rochester 7. Tautz H (1971) Warmeleitung + Temperaturausgleich. Verlag Chemie, Weinheim

16 Superposition Method in One-Dimensional Transient Heat Conduction Problems

The subject of Chap. 16 is the superposition method. The chapter contains formula derivations for Duhamel integral and demonstrates how one can apply them in practice in order to determine temperature in the half-space when surface or medium temperature is time-variable. Also, formulas are derived for the half-space temperature, with an assigned surface heat flux, whose changes in time are depicted by various functions. Furthermore, authors determine formulas, which are applied in transient methods for measuring a heat transfer coefficient, when the half-space surface is heated by a step-changing heat flow in time and which, simultaneously, gives off heat by convection to surroundings. Computational programs are developed. Computational examples demonstrate, among others, how paper is heated in a xerographic photocopier, which is treated as a semiinfinite body.

Exercise 16.1 Derivation of Duhamel Integral Derive a formula for a Duhamel integral, using the superposition method.

Solution When surface temperature of a body, heat flux or the temperature of a surrounding fluid are a function of time, then temperature distribution inside the body is determined by means of the Duhamel integral. This integral derives from the superposition principle and can be applied to linear transient heat conduction problems when initial temperature of the body is uniform and equals To. In order to determine temperature field when surface temperature is time-variable, To + f (t) it is necessary to determine u(r,t) by solving a transient heat conduction problem when surface temperature T, undergoes a unit step-increase.

470

16 One-Dimensional Transient Heat Conduction Problems

t0.

Likewise, the function u(r,t) of temperature distribution inside a body, with a unit step-increase in heat flux on the body surface, is needed when the heat flux J(t) = q(t) on the body surface is a function of time, i.e. when

O, { q= 1 W/m 2

t0.

If medium's temperature To + f(t) is time-variable when convective heat transfer is set on the body surface, the function u(r,t) is a temperature distribution inside the body when the medium's temperature Tcz undergoes a unit step-increase

tO and the value of heat transfer coefficient ais constant. The function transientf(t) is approximated by a stepped line (Fig. 16.1). It is assumed that

s t s (}1 (}1 S t s (}2 (}2 S t s (}3

fi = f( (}o + (}1/ 2 ) , 12 = I[B1 +(B2-BI}/2 J,

(}o

h =I[ B2 + (B 3 -B2 )/2 J,

On the basis of the superposition principle, temperature distribution inside the body at any point r and time t = tM is the sum of all parts that derive from individual components f(t) fromj. to t,

T(r,tM )=10 +Ji[u(r,tM -Bo)-u(r,tM -fA)J+

J

+12 [u(v.t« - fA) -u(r,tM - ( 2) +

where u(r,t - (}M) = u(r,O) = 0

and

(4)

Exercise 16.1 Derivation of Duhamel Integral

471

j(/)

/3 - - - - - - -

---t

.Ii /1 1--..,jIC--I

Fig. 16.1. Approximation of changes in functionf(t) by means of the stepped line

Equation (4) can be written in the form ~

T (r.t« ) = To + L..Jfn n=l When 110n= (On - 0n-) t

=t

~

u{r,tM-On-l)-u{r,tM-On) 110n. 11 On

(5)

0, then from (5) one obtains the following for

M

T{r,t)=10+ t f{O) [au{r,t-O)] dO. o ao

(6)

au{r,t-O) _ au{r,t-O) ao at

(7)

f

Because

Equation (6) can be written as follows:

T(r,t)=10+ ff(B)au(r,t-B) dB. o

at

(8)

Equation (8) is a Duhamel integral. For the boundary condition of 1st or 3rd kind and non-zero initial temperature To functionf(t) is the excess of surface temperature T/t) above the initial temperature To or the excess of medium's temperature Tcz(t) above the initial temperature To' i.e.

f{t)=Ts{t)-To,

(9)

f ( t) = r: (t ) -10 .

(10)

472


In the case of the boundary condition of 3rd kind, the Duhamel integral (8) has the form

fn-

T(r,t)=To+ JLTcz(t)-1O o

]au(r,t-O) dO. at

(11)

Similar operation is performed for the boundary condition of 1st kind, when the following expression is obtained from (8) once (9) is accounted for:

T(r,t)=10+ KTs(t)_To]8u(r,t-O) dO.

(12)

at

o

Alternative form of (8) can be obtained from (4) when individual terms are grouped in a different way

T(r,tM )=To + jiu(r,tM -OO)+(f2 - ji)u(r,tM -Bt)+ +... +(fM - fM-I)u(r,tM -OM-I).

(13)

Equation (13) can be written in the form

f

T( r.i« ) = To +

n=l

where fa

=0 i 0 =O. For t = t 0

M

In - In-l u( v.t« - On-I) !:lOn ilOn

(14)

and ilOn ~ 0 one has

T(r,t)=To+

fdf(B) u(r,t-O)dO. dB

t

(15)

o

This is the secondform of the Duhamelfunction. The choice between (8) or (15) for the subsequent calculations can lead to different solutions of the same problem that may differ in the rate of convergence of the infinite series present in these solutions.

Exercise 16.2 Derivation of an Analytical Formula for a Half-Space Surface Temperature when Medium's Temperature Undergoes a Linear Change in the Function of Time Derive a formula for the half-space surface temperature, using the Duhamel integral, if temperature of a medium is defined by function T,(t) = To + bt, where bis a constant. Thermo-physical properties of the medium, A, c and p, are temperature invariant.

Exercise 16.2 Derivation of an Analytical Formula

473

Solution The second form of the Duhamel integral is used for the calculation (Ex. 16.1)

T(x,t)=To +

tJd[r, (e) -10] u(x,t-B)dB. o

(1)

dB

Accounting that

_d(_Tf_-_];_O) = _d(_bB_) = b

dB

(2)

dB

and that the expression for the surface temperature of the half-space, when medium's temperature undergoes a step-increase, is

(a r-;J

T(O,t)-To Tcz-To

----=1-erfc -vat e

A

a~~t ~

(3)

one can determine temperature distribution from (1). In order to determine function u(O,t), which is surface temperature when medium's temperature undergoes a unit step-increase and initial temperature is at zero, one assumes in (3) that u(O,t)=T(O,t), Tcz=1°C, To=O°C and obtains a2at

u( O,t) =1- erfc ~

(

j;i

(4)

e)}.

J

By accounting for (2) and (3), (1) has the form

l

(

T(O,t) =10 +b llI-erfC ~ ~a(t-e)Jr>: " . dB.

(5)

Noting that for erfc x = 1 - erf x, and subsequently integrating by parts leads to a new form of (5), t

a 2 a(t-B)

{[I-erf (~ ~a(t-e)J] fe-"t2-dBJ] -Jde I-erf ~~a(t-e) fe- "t2- dB .

T(O,t) =10 +bt-b

2

t

d [(

t

a

a(t-B)

}

(6)

474


If the expressions below are evaluated a

2

A2 a 2 a(t- B) dB = - - e .,t2 a 2a '

a(t- B)

Je

.,t2

(7)

(8)

Equation (6) can be written in the following form:

A2

T(O,t) =1'0 +bt-b {

a

-[l-erf(~ ~a(t-O) )]a2a

2

a(t-B)

t

e-.,t2- 0 -

(9)

While calculating derivative (8), it has been accounted for that 2 e _x 2 . -d ( erfx ) = -

(10)

J"i

dx

After transformations, (9) can be written as follow

(11)

hence, after accounting that t

t

f(t-Ot/2 dO=-2(t-O)1/t =2J(

(12)

o

one has

1-erf (a -J;;i J] bA e

2

2

2

bAT(O,t) =To +bt+a 2a

-

[

A

-2-

a a

a

;t -

A

2bAJi ~. (13) a na

Exercise 16.2 Derivation of an Analytical Formula

475

Introducing the new variable

a 2 at

(14)

1]=7'

the (13) for temperature distribution (13) assumes the form

T (0, t)

= To + bt -

q

~ {[1- erf (..F)Je -I} - ~.

(15)

Once dimensionless temperature is introduced *

T(O,t)-To

(16)

T =---ht

Equation (15) can be written as follows

T*

=1- ~[(I-erf..F)eq -IJ- k '

(17)

where 1] is expressed by (14). The calculated temperature T(1]) is presented in Table 16.1. Table 16.1. Dimensionless half-space surface temperature T* = [T(O,t) - To]/(bt) when medium's temperature is defined by Tcz(t) = To + bt

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19

0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0 1.1 1.2 1.3 1.4 1.5 1.6 1.7 1.8 1.9

0.19597 0.25793 0.29981 0.33186 0.35792 0.37989 0.39890 0.41563 0.43056 0.44404 0.45631 0.46756 0.47795 0.48759 0.49657 0.50498 0.51288 0.52032 0.52735

20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38

2.0 2.1 2.2 2.3 2.4 2.5 2.6 2.7 2.8 2.9 3.0 3.1 3.2 3.3 3.4 3.5 3.6 3.7 3.8

0.53401 0.54034 0.54636 0.55210 0.55759 0.56283 0.56786 0.57269 0.57732 0.58179 0.58608 0.59023 0.59423 0.59809 0.60183 0.60545 0.60895 0.61235 0.61565

39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57

3.9 4.0 4.1 4.2 4.3 4.4 4.5 4.6 4.7 4.8 4.9 5.0 5.1 5.2 5.3 5.4 5.5 5.6 5.7

0.61885 0.62196 0.62499 0.62793 0.63079 0.63358 0.63629 0.63894 0.64152 0.64404 0.64651 0.64891 0.65126 0.65355 0.65580 0.65799 0.66014 0.66224 0.66430

476


Table 16.1. cont

58 59 60 61 62 63 64 65 66 67 68 69 70 71 72

5.8 5.9 6.0 6.1 6.2 6.3 6.4 6.5 6.6 6.7 6.8 6.9 7.0 7.1 7.2

0.66632 0.66830 0.67024 0.67214 0.67400 0.67583 0.67762 0.67938 0.68111 0.68281 0.68448 0.68612 0.68773 0.68931 0.69087

73 74 75 76 77 78 79 80 81 82 83 84 85 86 87

7.3 7.4 7.5 7.6 7.7 7.8 7.9 8.0 8.1 8.2 8.3 8.4 8.5 8.6 8.7

0.69240 0.69391 0.69539 0.69685 0.69828 0.69969 0.70109 0.70246 0.70380 0.70513 0.70644 0.70773 0.70900 0.71026 0.71149

88 89 90 91 92 93 94 95 96 97 98 99 100

8.8 8.9 9.0 9.1 9.2 9.3 9.4 9.5 9.6 9.7 9.8 9.9 10.0

0.71271 0.71391 0.71510 0.71626 0.71742 0.71856 0.71968 0.72079 0.72188 0.72296 0.72403 0.72508 0.72612

One needs to carry out a large number of transformations in order to determine temperature distribution by means of the Duhamel integral. It is much easier to determine the distribution by applying Duhamel integral calculated by means of approximation using the rectangles method. Temperature transient with a unit function can also be in such a case numerically calculated, e.g. by means of the difference method or finite element method.

Exercise 16.3 Derivation of an Approximate Formula for a Half-Space Surface Temperature with an Arbitrary Change in Medium's Temperature in the Function of Time Determine a formula for surface temperature of a body with a convective boundary condition and time-variable medium's temperature Tcz(t) and constant heat transfer coefficient a. Treat the body with an arbitrary shape as a semi-infinite body, while assuming that the heating or cooling processes are short-lasting. Determine the value of heat transfer coefficient on the surface of complex-shape bodies [3-5] by means of a formula for surface temperature of a semi-infinite body. The value of the heat transfer coefficient a is chosen in such way that both, the body's measured surface temperature Ts.z(t) and calculated surface temperature Ts.z(t) are equal after p p time tp from the beginning of the heating or cooling process. Body surface temperature is frequently measured by means of liquid crystals.

Exercise 16.3 Derivation of an Approximate Formula

477

Solution A diagram of a semi-infinite body is shown in Fig. 16.2. T /'

x

Fig. 16.2. A diagram of a semi-infinite body

To determine body surface temperature, (15) is used; it is derived in Ex. 16.1. Backward approximation of the derivative df/dBby a difference quotient yields (14), from which, after transformations, (13), Ex. 16.1, is obtained. Equation (13), in Ex. 16.1, was a starting point for the derivation of the Duhamel integral. Surface temperature T, = T(O,t) is, therefore, formulated as follows:

Temperature of the medium Tcz(t) is approximated by a stepped line (Fig. 16.3). Function u (O,t) is a body surface temperature when the medium's temperature undergoes a unit step-increase.

u(O,t) =

1-[1- erf( ~ Fi)] ea~~t

The coordinates of temporal points ~, in which temperature TCZ,i = measured, are indicated in Fig. 16.3. Once we account for

ji = ~~z(I,O)

(2) Tcz(~)

is

(3)

in (1) and

ji -

ii-I = ~~z(i,i-l) = Tcz,i -

Tcz,i-l,

i=2, '" M,

(4)

478


~Tcz(l,O)

o

E)j

Fig. 16.3. Approximation of temperature changes in a medium Tc/t) by a stepped line

andthe influence function (2), we have

Is(tM)=To+ I 1-exp [a a(t -0.)] A 2

M {

M

2

1

X

1=1

x

[1- erf

[ a~a(tM -()i) J]} A

(5)

· .1.T"Z(i,i-l)'

If,

(6) then (5) can be written in the form

t

Is (~M )-To= {l-exp[ ~M (1- ~

x[1- erf ~M (1- ~ )]}.1.T"Z(i,i-l).

)]x (7)

Using (5), one can determine heat transfer coefficient a while accounting for the medium's time-variable temperature Tcz(t). By measuring halfspace surface temperature in time tM by means of the liquid crystals and by comparing it to temperature calculated from (5), one is able to determine a from the following non-linear algebraic equation

Exercise 16.4 Temperature of a Medium Undergoes a Linear Change

t., (tM )- t., (tM ) = 0 ,

479

(8)

where Ts,o(tM ) is the temperature given by (5), while Ts,/tM ) a measured halfspace surface temperature. For details about the conducted experiment refer to papers [3+5].

Exercise 16.4 Definition of an Approximate Formula for a Half-Space Surface Temperature when Temperature of a Medium Undergoes a Linear Change in the Function of Time Temperature of a medium, which heats up a half-space whose initial temperature is constant and is Toincreases according to formula Tcz(t) = To + bt, where b is the constant heating rate. Calculate half-space surface temperature by means of (5) from Ex. 16.3. Present calculation results in the form T' = T*(17M)' where T = [T(O,t) - To]/(btM). Compare calculation results with the results presented in Table 16.1, which were obtained by means of the analytical (17) (Ex. 16.2).

Solution Temperature changes in the medium are presented in Fig. 16.4. From the above diagram, one can see that I1Tcz(i,i-l)

= b( ()i -

(1)

()i-l) .

a b=tga

~TcZ(i,i .... l)

€');.... l

(9,

Fig. 16.4. Temperature changes in a medium formulated as Tcit) = To + bt

480


If time interval tM is divided into M number of equal sections, then

/1 ()i-l ,i

= ()i -

()i-l

tM

=-,

M

i=I,2, ... , M

(2)

i = 0, 1, 2, ... , M.

(3)

and Ll

oi

·A Ll .tu = lilUi-l ,i = 1M- ,

Equation (7) from Ex. 16.3 can be written in the form

T *M

= T(O,tM )-10 btu

f{ [(

1 =-~ M

l-exp

17M

J]

i 1--

i=l

x

M

(4)

X[l-errfTI)]}, where

(5)

Table 16.2. Half-space surface temperature calculated by means of the analytical (17) (Ex. 16.2) and approximate (4) Entry no. 17M 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19

17M) 0.5 0.35789 1.0 0.44401 1.5 0.49654 2.0 0.53398 2.5 0.56280 3.0 0.58605 3.5 0.60541 4.0 0.62192 4.5 0.63625 5.0 0.64887 5.5 0.66010 6.0 0.67020 6.5 0.67934 7.0 0.68769 7.5 0.69535 8.0 0.70241 8.5 0.70896 9.0 0.71505 9.5 0.72074 10.0 0.72608

17M) 0.35792 0.44404 0.49657 0.53401 0.56283 0.58608 0.60545 0.62196 0.63629 0.64891 0.66014 0.67024 0.67938 0.68773 0.69539 0.70246 0.70900 0.71510 0.72079 0.72612

8[%]

0.00838 0.00676 0.00604 0.00562 0.00533 0.00512 0.00661 0.00643 0.00629 0.00616 0.00606 0.00597 0.00589 0.00582 0.00575 0.00712 0.00564 0.00699 0.00694 0.00551

Exercise 16.5 Application of the Superposition Method

481

Calculations were done for different values of 17M when the entire time interval tM was divided into a number of M = 100 subsections. The comparison of temperature Ta * (O,17M ) calculated from the approximate (4) with temperature T,* (O,17M ) calculated by means of the analytical (17) (Table 16.1, Ex. 16.2) is presented in Table 16.2. Also, surface temperature measurement error was calculated by means of the approximate (4) e=

Te(O,tM )-Ta(O,tM) ·100% Te(O,tM)

(6)

From the analysis of results presented in Table 16.2, it is evident that a discrete form of the Duhamel integral ((5), Ex. 16.3) ensures high calculation accuracy. The main attribute of (5) is that it can be applied in cases when temporal temperature transients of a medium Tc/t) are complex.

Exercise 16.5 Application of the Superposition Method when Initial Body Temperature is Non-Uniform Illustrate the superposition method in transient heat conduction problems when initial temperature is non-uniform qJ(x). Boundary condition of 1st kind is assigned on the plate butting front, i.e. temperature Ts' while boundary condition of 2nd kind on the back surface of the plate (Fig. 16.5).

Solution The determination of temperature distribution can be divided into two partial problems. In the first problem, we have to determine temperature distribution TI(x,t) when boundary conditions are homogenous (zero). In the case of boundary conditions of 1st kind, one assumes that surface temperature equals zero; for boundary conditions of 2nd kind, heat flux equals zero, while in the case of boundary conditions of 3rd kind, temperature of the medium Tcz equals zero. Initial temperature TI(x,t)=cp(x) is non-zero. In the second problem, one has to account for the real boundary conditions when initial condition is zero. The unknown temperature distribution T(x,t) is the sum of solutions of TI(x,t) and Tn(x,t). The superposition method described above will be illustrated on the basis of an example in which the temperature field is determined in the plate shown in Fig. 16.5. Plate temperature distribution is expressed by equation

482


1

er a2T

-; atax

(1)

2 '

with boundary conditions (2)

and

aT ax

(3)

=0, x=L

and initial condition

(4)

T( x,t )11=0 = q;>( x) · T

Fig. 16.5. A plate with thickness L, insulated on the back surface with nonuniform initial temperature c;i...x) and a surface temperature T, assigned for t > 0

In accordance with the superposition method, the solution to problems (1)(4) should have the form T ( x,t) = T; (x, t) + IiI ( x,t).

(5)

By substituting (5) into (1)-(4), one has

~ (an a at

Ja

+ aTrr =

at

2n

ax 2

2Trr

+a

ax 2

(6) '

(7)

Exercise 16.5 Application of the Superposition Method

+ aTn I

811 I

8x

ax

x=L

=0 ,

483

(8)

x=L

Tr (x,t)11=0 + Tn (x,t )11=0 = qJ( x)·

(9)

The initial-boundary problem (6)-(9) can be separated into two partial problems 1

a211

811

-; 81- ax 2

(10) '

Tr (x, t )Ix=o = 0 , 811

ax

= 0,

I

(11)

(12)

x=L

(13)

and 1 8Tu a

fit-

a 2Iil

ax 2

'

Tn (x,t)Ix=o =t: , aIiI

ax

= 0,

I

(14)

(15)

(16)

x=L

Trl (x,t)11=0 = 0 ·

(17)

The solutions to the problem (10)-(17) can be found, among others, in reference [9, 10]. Additionally, another simple method for solving problems (1)7(4) will be shown below. If we assume that the solution has the form

T(x,t)=Ts +U(x,t) and substitute it into (1)7(4), we have

(18)

484


1

au a2u

-; 81- ax 2

'

U(x,t)lx=o = 0,

aUI ax

-0

(19)

(20)

(21)

x--]:

and

U(x,t)lt=o =tp(x)-Ts.

(22)

The solution to the problem (19)-(22) can be found, among others, in references [7, 10]. Both methods presented above produce the same results.

Exercise 16.6 Description of the Superposition Method Applied to Heat Transfer Problems with Time-Dependent Boundary Conditions Describe how the superposition method is applied to heat transfer problems with time-dependent boundary conditions.

Solution If heat flux (boundary condition of 2nd kind), surface temperature (boundary condition of 1st kind) or medium's temperature (boundary condition of 3rd kind) change in time, then one can determine the solution of the problem by summing up (superposition) partial solutions obtained when boundary conditions are constant in time. Heat flux qs (I) on the body surface, surface temperature T/t) or temperature of the medium Tcz(t) is written as the sum of constant quantities or quantities that change in time according to simple functions. Below four examples are given to explain the superposition method, once qs (I) , Ts(t) and Tcz(t) are denoted by a common' symbol B(t).

Exercise 16.6 Description of the Superposition Method Applied

485

Example 1 We can determine temperature distribution with a boundary condition shown in Fig. 16.6a by summing up the solutions of partial problems with the boundary conditions shown in Fig. 16.6b and c, while accounting for the initial operation of a given boundary condition.

T ( x, t) = To , T( x,t) = T; (x,t - tI),

t s II ,

(1)

tl < t S t: ,

(2)

T ( x, t) = Ii ( x, t - tl) + IiI ( X, t - t: ), a)

b)

B

B

(3)

c)

Q)

B

®

+ o

o

o

Fig. 16.6. Expansion of function B(t) into two components

We can determine temperature by means of (1)-(3) and from the diagrams of body temperature transients with an assigned body shape and boundary conditions or we can analytically or numerically calculate temperature u(x,t) when a boundary condition is unit function. Once we assume (and that depends on the kind of the assigned boundary condi2 tions)that q.s = 1 W1m , Ts = 1°C or Tcz = 1°C, we can determine temperature transient u(x,t), also called the influence function. Temperature distribution with constant value B has the form

T(x,t)=Bu(x,t).

(4)

Once we account for (4), (1)-(3) can be written as follows:

T( x,t) = To,

t S ti,

(5)

486


T( X,/) = B1u (X,I- 11)'

(6)

T( x,t) = B1u (X,I -11) - B1u ( x,1 -t2),

(7)

Equations (5)-(7) enable us to calculate temperature at a any spatial point x and time t. Example 2

Function B(t) can be expressed as follows (Fig. 16.7): B ( I ) = B1

for

0 < I sit,

(8)

(9)

If the solutions of partial problems T1, TIl and TIll are known when boundary conditions are as given in Fig. 16.7a, then we can present the solution T as the sum of solutions to partial problems, while accounting for the initial stage of operation and duration of a given boundary problem. For individual partial problems, time is measured from the moment the boundary condition exerts its influence, i.e. as a time variable in problem I (Fig. 16.7b) time t will be assumed, in problem II (Fig. 16.7c) time (t - t), while in III (Fig. 16.8d) time (t - t2 ) . a) B",

B

B

.)

BI

-

B2

0

t,

/2

13 t

d)

c)

b)

CD

®

B

8}

8 3-B2

+ 0

®

B

13

t

11

t2

+

13

t

B2-B]

Fig. 16.7. Division of function B(t) into three components

t}

12

t,.) 1

Exercise 16.6 Description of the Superposition Method Applied

487

Example 3

The solution of a transient heat conduction problem, with the boundary condition shown in Fig. 16.8a, has the form

T ( x,I ) = Ti (x,I ) ,

o~ I ~ 11,

(11)

T ( x, I ) = Ti (x, I ) + Til (X, I - 11 ) ,

(12)

where TI' Tn and TIll are partial solutions, for which the changes in function B are presented in Fig. 16.8b, c and d. a)

c)

b)

B

d)

®

B

@

+

Fig. 16.8. Division of function B(t) into three components

Example 4

The solution of the transient heat conduction problem with changes in function B(t), presented in Fig. 16.9a, has the form

T ( x, I ) = Ti (x, I ) ,

0 5), one should take into consideration the fact that oscillations may occur.

Exercise 17.4 Formula Derivation for a Heat Flux Periodically Changing... 523

Exercise 17.4 Formula Derivation for a Heat Flux Periodically Changing in Time on the Basis of a Measured Temperature Transient at a Point Located under the Semi-Space Surface Determine a formula for periodically changing heat flux in time under the assumption that half-space surface temperature yet) is known from the readings taken as well as the temperature IE inside the half-space, within distance E ~ 8, where Sis the depth of heat flow penetration (Ex. 14.8) into the half-space interior. Thermo-physical properties of the semi-infinite body: A, C and p are constant.

Solution From the surfaces of combustion chambers in combustion engines and from the surfaces of pipes submersed in a fluid bed, heat flux q(t) (Fig. 17.3) can be divided into two components: q [steady-state; independent of time] and qn(t) [transient; changes periodically in time]. (1) T

_

q~ f(t)

o

x

Fig. 17.3. Diagram of the location of temperature measurement points

If the frequency of heat flux changes qn (t) is high, then the temperature and heat flux change in time only in the vicinity of the element's surface, at a depth of about 1+2 mm, while the temperature inside the element remains constant with time. In order to determine components q and qn(t), temperature is measured at two points (Fig. 17.3): on the heat-transferring surface (x = 0) and within distance x = E from this surface. Distance E

524

17 Transient Heat Conduction in a Semi-Infinite Body

must be selected in a way that temperature at such point is independent of time, i.e. so that fast-changing processes, which occur on the element's surface, would be completely suppressed at this point. In the case of combustion engines, it is usually assumed that E ~ 3 mm. Temperature distribution in the region 0 s x s E is defined by the heat conduction equation [12] 8 2T 8x 2

-

1 8T a at

(2)


Tlx=o =f(t)=7+y(t),

SsE.

Tlx=E = fE = const,

(3)

(4)

It is not necessary to know the initial condition, since only the quasistationary solution independent of the initial condition will be examined here (Ex. 14.6). The effect of the initial condition on the determined temperature distribution already vanishes after few cycles. Due to the linearity of the problem (2)-(4), superposition principle is applied to solve it

T(x,t) =T (x) + T; (x,t) ,

(5)

where T (x) is the steady-state solution component, while Tn(x,t) a timedependent component (quasi-steady component). Once (5) is substituted into (3)-(4), two partial problems are obtained; the first one allows for determining temperature f (x ) d2f

(x)

--2-=0, dx

OsxsE,

fL=o = 7, flx=E = fE,

SsE,

(6) (7) (8)

the second for determining quasi-steady component Tn(t) 2

8 Tn 8x

2

1 ot:

--;81'

OsxsE,

t; Ix=o = y(t) ,

(9) (10)

Exercise 17.4 Formula Derivation for a Heat Flux Periodically Changing

525

Boundary condition (11) can be replaced by two conditions (12)

aT I = 0 at x~oo ' n

(13)

where the depth of heat penetration t5 is smaller than E and the boundary condition at point x = E can be treated as a condition at an infinitely large distance from the half-space surface. Steady-state temperature distribution, which is the solution to the problem (6)-(8), has the form (14)

In terms of the heat flux measurement on the inner cylinder surface of a combustion engine or a compressor, periodic temperature changes yet) are approximated by means of the Fourier series N

y(t) = I[ Ak cos( kOJt) + Bk sin ( kOJt)] '

(15)

k=l

where

y(t)=f(t)-l,

(16)

1p

1 = - Ji(t)dt,

(17)

Po

~

2P

=-

Ji(t)cos(kOJt)dt,

k=I,2, ...,N,

(18)

k=I,2, ...,N,

(19)

Po

2P

B, = - Ji(t)sin(kOJt)dt, Po

2Jr

0)=-

P

while p is the period.

,

526


If the duration of a single cycle, suction-compression-decompressionexhaust corresponds to two crankshaft revolutions, then frequency OJ is equal to the half of crankshaft's angular velocity, i.e. OJ = Jrnl60 lIs, where n is the number of shaft revolutions per minute. The solution to the problem: (9), (10), (12), (13) while accounting for (15), can be easily determined using the results obtained in Ex. 14.6. The solution has the form then

t: (x,t) = fexp(-x [k;Jx V~

k=l

(20)

It is a quasi-steady solution, which describes steady-state temperature fluctuations. This solution is not valid at the initial moments of the transient process, when the initial temperature distribution has an effect on temperature distribution in the half-space. By accounting for (14) and (20) in (5), one has

T(x,t) =7 + IE -7 x+ fexp(-x~klV E

2a

k=l

Jx (21)

Heat flux is expressed as

(mOJJ

. aT]- jE +AL..J ~mOJ q(X,t)=-A-=A -exp -x -

ax

E

k=l

2a

x{ h [COs(klVt-XmJ-Sin(klVt-XmJ+ -s. [COs( ken -

xmJ

+

Sin( kcot - xmJ]}.

Formula for surface heat flux has the form

x

2a

(22)

Exercise 17.5 Deriving a Heat Flux Formula on the Basis

527

q( O,t) = A1- IE + ifJkW {~[cos( kwt) - sin ( kwt)] + E

k=l

2a

(23)

+Bk [ cos( kwt) + sin ( kwt) J} . Coefficients of the Fourier series, A k, Bk, k = 1, ..., N and average surface temperature f are determined when the measured surface temperature transientf(t) is approximated by means of the Fourier series (trigonometric polynomial) N

/(t) = 1 + I[ ~ cos( kwt) + s, sin ( kwt) J.

(24)

k=l

To determine A k , Bk' k = 1, ..., N, one can use the programs from IMSL library [7] or the Table Curve software package[ll].

Exercise 17.5 Deriving a Heat Flux Formula on the Basis of Measured Half-Space Surface Temperature Transient, Approximated by a Linear and Square Function Determine formulas for heat flux on the surface of a construction element, which can be considered as a semi-infinite body, if the measured surface temperature of the element can be approximated by the following functions: a) yet) = To + bt, b) yet) = To + bt',

(1) (2)

where, To is the initial temperature of the element, while a and b are constants. Determine heat flux by means of (7) derived in Ex. 17.3.

Solution If the measured surface temperature is approximated by a polynomial 2

s

Y (I) = Ao + All + A2 / + ..... + As/ ,

then heat flux is defined by (7) derived in Ex. 17.3

(3)

528


ri)

r; +-A 4 2"JtG +-A 8 3"Jtr: +-~"Jt' 64 t: +-As"Jr 128 q. () t = 2 ~ACP - - ( AIvt

3

Jr

5

35

63

. (4)

In an instance when function a) is used for approximation, coefficients of the polynomial (3) are

Ao = 10 , Al = b, A2 = A3 = ~ = As = 0 .

(5)

From (4), one has

q(() = 2b~ A; t

.

(6)

In a case when function b) is used for approximation, the coefficients of the polynomial (3) are

Ao = 10, Al = 0, A2 = b, A3 = ~ = As = 0 .

(7)

From (4), one obtains

q(()=~b~ACP (3 . 3

(8)

Jr

Equations (6) and (8) are both the same as the analytical formulas presented in reference [16].

Exercise 17.6 Determining Heat Transfer Coefficient on the Plexiglass Plate Surface using the Transient Method Determine heat transfer coefficient on the basis of a surface temperature measurement of the plexiglass plate, which is first heated to an initial temperature of To = 66°C and then suddenly cooled by an airflow, which moves along the plate surface at the temperature of Tcz = 20 o e.

a -0-f-7----,-~

S

~....---r-r---r4t:-r-___7_~---~

~ ~__'__lf____'--"-----'-~---[

x

plexiglass

Fig. 17.4. Diagram of the heat transfer coefficient measurement

Exercise 17.6 Determining Heat Transfer Coefficient

529

A plate, whose thickness is L = 1.27 ern (Fig. 17.4) can be regarded as a semi-infinite body, while accounting for the fact that the time of heat penetration to the opposite plate surface is about 2 min. Plate surface temperature measured by means of the liquid crystals is Tsm =47.9°C after time tm = 87 s from the beginning of its cooling process. Assume the following thermo-physical properties of the plexiglass for the calculation: A = 0.187 W/(m·K), p = 1180 kg/m', e = 1440 J/(kg·K) (Ex. 17.1, Table 17.1). Use graphical and numerical methods to solve this exercise.

Solution The method for determining a is discussed in Ex. 17.1.

Graphical method Temperature diffusivity coefficient a = }J(ep) is a = (0.187/(1180·1440) = 7 2/s. 1.08286.10- m Because dimensionless half-space surface temperature ()sm is

To Tcz - 10

(}sm = Tsm -

= 47.9 - 66 = 0.3935,

20 - 66

then from Fig. 14.2 in Ex. 14.4 for a calculated value of ~m and x/(atm )l/2 = 0, one approximately obtains

a .Jatm ~ 0.6, A

hence,

a

e

0.6A = 0.6·0.184 =35.97~. 2·K .Jatm .J1.08286.10-7.87 m

Value a can be determined more accurately by the numerical method.

Numerical method Unknown value a is the root of a non-linear algebraic (4) in Ex. 17.1, which will be written in the form

F(a)=O,

(1)

where

(a -: exp [a Aat 2

F ( a ) = t; _~

10 -1+ [ 1-erf -'\Iatm 10 A

m

- - 2 -) .

(2)

530


After substitution of the numerical values, function F( a) has the following form:

F(a)= 47.9-66 -1+ [ l-erf 20-66

xexp

(a) - - -vl.08286·10- 7 ·87] x 0.187 I

a 2 ·1.08286·10-7 .87J (

0.1842

'

F( a) = -0.606522 + [1- erf( 0.016681a) Jexp( 2.782633 ·10--4 a 2 ) . (3) Equation (3) can be solved using one of the commonly available methods, such as the interval search method, interval bisection method, Newton method, or secant method. Table 17.2. Transient of function F( a) formulated in (3)

25.00 25.10 25.20 25.30 25.40 25.50 25.60 25.70 25.80 25.90 26.00 26.10 26.20 26.30 26.40 26.50 26.60 26.70 26.80 26.90 27.00 27.10 27.20 27.30 27.40 27.50 27.60 27.70 27.80 ~7.92-

0.054319 0.053357 0.052398 0.051441 0.050486 0.049534 0.048584 0.047636 0.046690 0.045747 0.044806 0.043868 0.042931 0.041997 0.041065 0.040135 0.039208 0.038283 0.037360 0.036439 0.035520 0.034604 0.033690 0.032778 0.031868 0.030960 0.030054 0.029151 0.028250

28.00 28.10 28.20 28.30 28.40 28.50 28.60 28.70 28.80 28.90 29.00 29.10 29.20 29.30 29.40 29.50 29.60 29.70 29.80 29.90 30.00 30.10 30.20 30.30 30.40 30.50 30.60 30.70 30.80

0.026454 0.025559 0.024666 0.023776 0.022887 0.022001 0.021116 0.020234 0.019354 0.018476 0.017600 0.016726 0.015854 0.014984 0.014116 0.013251 0.012387 0.011525 0.010665 0.009808 0.008952 0.008098 0.007247 0.006397 0.005549 0.004704 0.003860 0.003018 0.002178 40_. 0_.0~7"""",3"""",51_3.Q.99 _._ ..._°"""",.2213_

31.00 31.10 31.20 31.30 31.40 31.50 31.60 31.70 31.80 31.90 32.00 32.10 32.20 32.30 32.40 32.50 32.60 32.70 32.80 32.90 33.00 33.10 33.20 33.30 33.40 33.50 33.60 33.70 33.80

0.000504 34.00 -0.000330 34.10 -0.001162 34.20 -0.001992 34.30 -0.002820 34.40 -0.003647 34.50 -0.004471 34.60 -0.005294 34.70 -0.006114 34.80 -0.006933 34.90 -0.007750 35.00 -0.008565 35.10 -0.009378 34.00 -0.010189 34.10 -0.010999 34.20 -0.011806 34.30 -0.012612 34.40 -0.013416 34.50 -0.014218 34.60 -0.015018 34.70 -0.015816 34.80 -0.016613 34.90 -0.017407 35.00 -0.018200 35.10 -0.018991 35.20 -0.019780 35.30 -0.020568 35.40 -0.021354 35.50 -0.022137 35.60 ]]_.~_O._ _ -QJ"""",.)2"""",29_20_.~5·Z9_.

-0.023700 -0.024479 -0.025255 -0.026030 -0.026804 -0.027575 -0.028345 -0.029113 -0.029879 -0.030644 -0.031407 -0.032168 -0.023700 -0.024479 -0.025255 -0.026030 -0.026804 -0.027575 -0.028345 -0.029113 -0.029879 -0.030644 -0.031407 -0.032168 -0.032928 -0.033685 -0.034441 -0.035196 -0.035948 -0.036699 ~~w.-

Exercise 17.6 Determining Heat Transfer Coefficient

531

Table 17.2. (cont.)

35.80 35.90 36.00 36.10 36.20 36.30 36.40 36.50 36.60 36.70 36.80 36.90 37.00 37.10 37.20 37.30 37.40 37.50 37.60 37.70 37.80 37.90 38.00

-0.037449 -0.038196 -0.038942 -0.039687 -0.040429 -0.041170 -0.041910 -0.042647 -0.043383 -0.044118 -0.044850 -0.045582 -0.046311 -0.047039 -0.047765 -0.048490 -0.049213 -0.049935 -0.050654 -0.051373 -0.052089 -0.052805 -0.053518

38.20 38.30 38.40 38.50 38.60 38.70 38.80 38.90 39.00 39.10 39.20 39.30 39.40 39.50 39.60 39.70 39.80 39.90 40.00 40.10 40.20 40.30 40.40

-0.071533 -0.072206 -0.072877 -0.073547 -0.074215 -0.074882 -0.075548 -0.076212 -0.076874 -0.077536 -0.078195 -0.078854 -0.079511 -0.080166 -0.080821 -0.081473 -0.082125 -0.082775 -0.083423 -0.084071 -0.084717 -0.085361 -0.086004

-0.05494140.60 -0.05564940.70 -0.05635740.80 -0.05706240.90 -0.05776741.00 -0.05846941.10 -0.05917041.20 -0.05987041.30 -0.06056841.40 -0.06126541.50 -0.06196041.60 -0.06265341.70 -0.06334541.80 -0.06403641.90 -0.06472542.00 -0.06541242.10 -0.06609842.20 -0.06678342.30 -0.06746642.40 -0.06814742.50 -0.06882742.60 -0.06950642.70 -0.07018342.80

43.00 43.10 43.20 43.30 43.40 43.50 43.60 43.70 43.80 43.90 44.00 44.10 44.20 44.30 44.40 44.50 44.60 44.70 44.80 44.90 45.00

-0.087286 -0.087925 -0.088563 -0.089199 -0.089834 -0.090468 -0.091100 -0.091731 -0.092361 -0.092989 -0.093616 -0.094242 -0.094866 -0.095489 -0.096111 -0.096731 -0.097350 -0.097968 -0.098585 -0.099200 -0.099814

0,08,..-----------------, F(a)

0,04

o,oo+---------::ItP-----------1

-0,04

29 a* 33

37

41

45

a [W/(m2'K)]

Fig. 17.5. Function F(a) in the interval 25 W/(m 2·K) S a S 45 W/(m 2·K), 2·K) a* = 31.06 W/(m

532


In the given case, the simplest method was chosen: the interval search method. Root a of (3) will be searched for in the interval [25, 45] with a 2·K). step ~a= 0.1 W/(m The function F( a) is shown in Table 17.2 and in Fig. 17.5. It is clear from both, the table and Fig. 6.2 that the unknown value a lies in the inter2·K) 2·K). S a S 45 W/(m By searching this interval with a val 25 W/(m 2·K), smaller step, which equals ~a = 0.01 W/(m one can assume that the 2·K). unknown value is a = 31.06 W/(m

Exercise 17.7 Determining Heat Flux on the Basis of a Measured Time Transient of the Half-Space Temperature, Approximated by a Piecewise Linear Function Determine the heat flux q(t) transient on the half-space surface. Assume that the half-space surface temperature transients shown in Table 16.5 and Fig. 16.20, in Ex. 16.11, are an accurate and approximate measurement 2·K·sl/2 data for the calculation. Also assume that (Acp)l/2 = 35968 J/(m ) . Present calculation results in the form of graphs; use them to compare calculated and exact heat flux values. Enclose a computational program in FORTRAN language. Use, in the calculation, (8) and (16) from Ex. 17.2 for the exact and approximate measurement data, respectively. Carry out calculations for a time step ~t = 1 s. For disturbed measurement data, carry out calculations with and without smoothing using the seven-point digital filter given by (9)-(12), Ex. 17.2.

Solution Program for determining heat flux in time PROGRAM p17_7 real temp(61),temp_z(61),temp_w(61) Pi=3.14159 p_l_c_ro=35968. dt=l. OPEN(1,FILE='p17_7.in',STATUS='OLD') OPEN(2,FILE='p17_7.out',STATUS='OLD') do i=1,61 read(1,300) t,temp(i),temp_z(i) write(2,300) t,temp(i),temp_z(i) temp_w(i)=temp_z(i) enddo

Exercise 17.7 Determining Heat Flux on theBasisof a Measured Time

300

533

call filtr_7t(61,ternp_w) do rn=1,60 surna=O. surna z=O. surna w=O. do i=l,rn surna=surna+(ternp(i+l)-ternp(i))/ & (sqrt(dt*(rn)-dt*(i-l))+sqrt(dt*(rn)-dt*(i))) surna_z=surna_z+(ternp_z(i+l)-ternp_z(i))/ & (sqrt(dt*(rn)-dt*(i-l))+sqrt(dt*(rn)-dt*(i))) surna_w=surna_w+(ternp_w(i+l)-ternp_w(i))/ & (sqrt(dt*(rn)-dt*(i-l))+sqrt(dt*(rn)-dt*(i))) enddo surna=surna*2.*p_l_c_ro/sqrt(Pi) surna_z=surna_z*2.*p_l_c_ro/sqrt(Pi) surna_w=surna_w*2.*p_l_c_ro/sqrt(Pi) write (2, *) (rn) *dt, surna, surna_ z, surna w enddo STOP FORMAT (F7.0,3x,F9.4,3x,F9.4) END SUBROUTiNE filtr_7t(np,T) INTEGER np PARAMETER (NPOINT=61) DiMENSiON T(NPOINT) DiMENSiON F(NPOINT) F(1)=1./42.*(39.*T(1)+S.*T(2)-4.*T(3)-4.*T(4)+ & T(5)+4.*T(6)-2.*T(7)) F(2)=1./42.*(S.*T(1)+19.*T(2)+16.*T(3)+6.*T(4)& 4.*T(5)-7.*T(6)+4.*T(7)) F(3)=1./42.*(-4.*T(1)+16.*T(2)+19.*T(3)+12.*T(4)+ & 2.*T(5)-4.*T(6)+T(7)) j=l DO i=4,np-3 F(i)=1./21.*(-2.*T(j)+3.*T(j+l)+6.*T(j+2)+7.*T(j+3)+ & 6.*T(j+4)+3.*T(j+5)-2.*T(j+6)) j=j+l ENDDO j=np-6 F(np-2)=1./42.*(T(j)-4.*T(j+l)+2.*T(j+2)+12.*T(j+3)+ & 19.*T(j+4)+16.*T(j+5)-4.*T(j+6)) F(np-l)=1./42.*(4.*T(j)-7.*T(j+l)-4.*T(j+2)+6.*T(j+3)+ & 16.*T(j+4)+19.*T(j+5)+S.*T(j+6)) F(np)=1./42.*(-2.*T(j)+4.*T(j+l)+T(j+2)-4.*T(j+3)-

534

17 Transient Heat Conduction in a Semi-Infinite Body & 4.*T(j+4)+8.*T(j+5)+39.*T(j+6)) DO j=l,np T(j)=F(j) ENDDO END

a) 3E+006 ~----

q

-----------,

[W/m2]

2E+006

lE+006 A

OE+000 J!r------L..--~----L..--~----&..---.o 20 40 t [s] 60

b) 3E+006.....------.....----------.,

q [W/m2]

2E+006

lE+006

OE+000

. ! r - - - - - - L . ._ _...I...-_---L.._ _. . . I . . . - _ - " - _ - - - M '

o

20

40

t [s] 60

Exercise 17.8 Determining Heat Flux on the Basis...

535

c) 3£+006 - - - - -.......- - - - - - - - - - - ,

q [W/m2]

2E+006

lE+006

OE+OOO

o

20

40

t [s] 60

Fig. 17.6. Determined heat flux on the half-space surface: a) exact measurement data, b) measurement data disturbed by random errors, c) measurement data disturbed by random errors, which are smoothed by means of the seven-point digital filter

From the analysis of results presented in Fig. 17.6, it is clear that the accuracy of the heat flux determination, by means of (8) from Ex. 17.2, is very high. From the analysis of results for the error-disturbed measurement data, shown in Fig. 17.6 band c, one can see that data smoothing by means of the digital filter considerably improves the accuracy of the obtained results.

Exercise 17.8 Determining Heat Flux on the Basis of Measured Time Transient of a Polynomial-Approximated Half-Space Temperature By means of (7), derived in Ex. 17.3, determine a transient of heat flux q(t) on the half-space surface by assuming that the measurement data disturbed by random errors is the data from Table 16.5, in Ex. 16.11. Assume 2·K·s l12 ) . Apply Table Curve for the calculation that (Acp)1/2 = 35968 J/(m program [11] to approximate measurement data by means of the m-degree polynomial. Carry out calculations for 3 degree (m = 3), 5 degree (m = 5) and 7 degree (m = 7) polynomials. Present calculation results on a graph and compare them with the exact heat flux transient.

536


Solution Measurement data is approximated by means of the Table Curve 2D v5.0 program; the following coefficients of the polynomial (1) in Ex. 17.3 are obtained: • 3 degree polynomial A o = -38.08713°C, At = 13.962632°C/s, 2 A 2 = 0.064750667°C/s , 3 A 3 = -0.0036616424°C/s ; • 5 degree polynomial A o = 11.145049°C, At = -4.9820027°C/s, 2 A 2 = 1.6606051°C/s , 3 A 3 = -0.05288742°C/s , 4 A 4 =0.00060050935°C/s , 6°C/s s As = -2.2763261·10; • 7 degree polynomial A o = -6.0269987°C, At = 11.172823°C/s, 2 A 2 =-1.5560632°C/s , 3 A 3 = 0.20486938°C/s , 4 A 4 =-0.009563855°C/s , s As = 0.00020718291 °C/s , 6°C/s6 A 6 = -2. 1616686·10, 9°C/s7 A 7 = 8.8072649·10• The comparison of the determined polynomial transients with the measurement data is presented in Fig. 17.7. The results of heat flux calculation done by means of (7) (Ex. 17.3) are presented in Fig. 17.8. From the analysis of results presented in Fig.17.8, it is clear that the highest accuracy is obtained for the 7-degree polynomial (m = 7).

Exercise 17.8 Determining Heat Flux on the Basis...

537

400.------------------, m=3 T[OC] 300

200

:6.

A I.:i

A

100

A

A

1.1

0

A

f

---y

-10°0

20

40

t [s]

60

40

I

[s]

60

400 m=5

TIOC]

300

200

100 1.1

o ._. . 100

f

---y

20

0

400...-----------------, TrOC]

m=7

300

200

100 A

o

f

---y

-100 . L - - _ . . . l - - _ - I . - _ - - ! - - _ - - I . - _ - - L . _ - - - J o 20 40 t [s] 60

Fig. 17.7. Approximation of the measurement data disturbed by random measurement errors by means of different m degree polynomials

538

17 Transient Heat Conduction in a Semi-Infinite Body 3E+006 r - - - - - - - x - - - - - - - - - - , m 3 2]

tj [\Vltn

2E+006

A

lE+006

_ _ _ (j exact

OE+OOO

cj calculated

-1 E+006

' - - - - _ - ' - - _ - - ' - _ - - > . ._ _' - - - _ - J o . - _ - - J

o

20

40

t [s]

60

3E+006 r------~---------,

mr S

tj [W'/111 2] 2E+006

lE+006

- - - (i exact

OE+OOO

6

--,1 E+O()6 ()

20

q calculated

40

t [5]

60

3E+006.---------------~

q·1-\1~.

Boundary condo of 1st or 3rd kind

g*(x,r,t)

tr

x r

has a point of origin in the cylinder /' - -, center)

~

=

= To

S(x,t)· C( r,t)·P(Z,t)

T(x,r,t) +Te(r,t)

e*(x,r,t) = P(x,t)·C(r,t)

T(x,r,t) To + Te(r,t)

=

+ TsCx,t)

+ T, (r.r)


577

Exercise 19.2 Formula Derivation for Temperature Distribution in a Rectangular Region with a Boundary Condition of 3rd Kind Using the superposition method, derive a formula for temperature distribution in an infinitely long rod with a rectangular cross-section 2b x 2d, and is heated or cooled by a medium at constant temperature Tcz (Fig. 19.3). Heat transfer coefficient on the side, which measures 2b in length is ab , while on the side 2d equals ad. Initial temperature of the rod is constant and equals To' while thermo-physical properties are temperature-invariant.

y

b

»
O. The upper integration limit equals J(t) in the case of a semi-infinite space. If temperature field is determined in an element with finite dimensions, for example in a plate (Fig. 20.1), then one can distinguish two heat transfer phases: the first one, when the depth of heat penetration is smaller than the wall thickness, i.e. J ~ L; the second, when J =L. For the first heat transfer phase, once we account for the conditions that arise from the depth of the heat penetration concept vet) = J(t), we have

T[v(t),tJ=To ,

(4)

aTI =0 ax x=v(t) ,

(5)

and once we account that wet) = 0 and dw/dt = 0, (3) assumes the form

~[cP5(ii -t; )J=-A aTI ' dt ax x=o

(6)

where average temperature 1i is defined as _

10

Ti =-

fT(x,t)m,

50

0~5~L.

(7)

In the second heat transfer phase J(t) = L, the temperature of the rear surface changes, i.e. TL=L = u(t) (Fig. 20.1). Equation (3) assumes the form

cpL dIn dt where

In

=

A(aTI _aTI ) ax x=L ax x=o '

(8)

is the average temperature equal to _

1L

IiI =- fTm. L

(9)

o

In order to determine temperature T(x,t) , one should assume a function form that approximates temperature distribution in both, the first and second heat transfer phase. Usually these are polynomials of 2nd or 3rd degree. Integral heat balance method can be also applied to non-linear heat conduction equations and non-linear boundary conditions [1]. When cp = !t(n and A =hen, then once integral transformation is applied

590

20 Approximate Analytical Methods T

9(T)= JcpdT

(10)

o

calculation method resembles the method used when constant thermal properties c, p and A are applied. Also in the case of heterogeneous materials, i.e. when cp = fJx) and A = hex), once integral transformation is applied x

dx (11)

m=f-i(x) it is possible to apply the heat balance method.

Exercise 20.2 Determining Transient Temperature Distribution in a Flat Wall with Assigned Conditions of 1st, 2nd and 3rd Kind Determine transient temperature field in a flat wall (plate) with boundary conditions of 1st, 2nd and 3rd kind. Assume that heat transfer conditions only change on the plate front face. Use the integral heat balance method to solve the problem.

Solution Plate temperature distribution is defined by the heat conduction equation 1 et

a2T

--;;at - ax

(1)

2 '


aTI -A-

ax x=o

+ P1Tlx:o = r14n (t)

,

(2)

(3) and by initial condition

Exercise 20.2 Determining Transient Temperature Distribution

591

Such formulation of boundary conditions enables one, by appropriately selecting coefficients, to assign temperature, heat flux or convective heat transfer on the plate surfaces, therefore, the boundary conditions of 1st, 2nd or 3rd kind respectively: a) boundary conditions of 1st kind

(5)

b) boundary conditions of 2nd kind

/31 =0,

-}., arl ax

= rl101 (t) = qOl (t), x=o

(6)

c) boundary conditions of 3rd kind

(7)

arl

-J-

ax

=

a2[rl x =L - Ta2 J.

x=L

According to the integral heat balance method, temperature distribution is determined in two phases. In the first heat transfer phase, when 0 S 5(t) s L, temperature distribution should be approximated by a polynomial of the second degree (8) Constants ao' a 1 and a2 are determined from the boundary condition (2) and from conditions

(9)

592

20 Approximate Analytical Methods

By substituting the determined constants into (8), temperature distribution in the first heat transfer phase has the form 1

Ii = 102 - - 8 2

/31 T()2 - r, T(B (I)

!P18+A 2

1 /31102 - r, 101 (I) 2

-----X,

28

+

/31T()2 - r, 101 (I )

x-

!PI8+A 2

(10)

0~x~8

!P18+A 2

and

T;

= 102,

8~x~L.

(11)

If (10) is substituted into (7) (Ex. 20.1) for average temperature ~, then the following equation is obtained

(12)

However, when (12) is substituted into (6) (Ex. 20.1) and boundary condition (2) is accounted for, one obtains, after transformation, the following differential equation to describe 8 (t):

(13)


593

In the second heat transfer phase, temperature distribution should also be approximated by a polynomial of the second degree (14) Once constants a.; a4 and as are determined from boundary conditions (2) and (3) and from condition (15) and again substituted into (14), one has

(16)

Accounting for (16) in (9) (Ex. 20.1), one obtains, after transformation

(17)

If (17) is substituted into heat balance (8) (Ex. 20.1), then differential equation is obtained that serves as a tool for determining u(t)

594


In the examples given, (13) and (18) will be solved for the few cases that are of particular importance in the field of engineering. Example 1

Tal (t) = Tal = const,

Ta2 = O. (19)

This case corresponds to a so called thermal shock in tanks or other constructions, when a wall, insulated on one side, is suddenly warmed-up or convectively cooled down on the other side. Temperature distribution in the first heat transfer phase is obtained once (19) is substituted into (10)

11=

Bi( 5) ( XJ2 ToI Bi(8)+2 1- g

Osxs5,

0,

s s s-u;

(20)

where Bi(5) = a 18lA. In the second phase, temperature distribution is obtained from (16) once (19) is allowed for

Bi(L) (XJ2 111= o() (ToI-U) 1-- +U, Bz L +2

L

(21)

2

where F0 1 = at/L ; time t l is a moment when 8 = L. The solution of (13), when initial condition is 5t=o = 0 and (19) accounted for, is

_1 + 1 _ 2 In Bi(o)+2 =Fo(o) 12 3Bi(O) 3[Bi(O)T 2 '

(22)

where Fo(5) =at/5 • Fourier number F0 1 is obtained once 8 = L is substituted into (22). Calculation of temperature distribution in the first phase is done in the following way. First we assume that 8, for example, 8= 0.5L, then we determine 2


595

time t from (22) that corresponds to the assumed value 8. (20) enables one to determine spatial temperature distribution. Following that (18) must be solved when initial condition is u(Fo) =O. Once we account for (19), we have

u (t) = t;

[1- e

-p'(Fo-FOI)

J,

(23)

where 2

3Bi{L)

(24)

f.1 = 3+Bi(L) .

One can easily observe, by comparing (23) to the analytical solution (Ex. 15.1), that J.l is an approximation of the first root of the characteristic equation

ctgz, =

;i ·

(25)

In order to evaluate the accuracy of the approximate solution (24), one should compare the first root of (25), determined from (24) with the exact values III * calculated in Ex. 15.2. Table 20.1. Comparison between the exact value of the first root III * of the characteristic (25) and approximate values III calculated from (24) Bi III

0.0316

~.0316

Bi

2.0 1.0954

0.002 0.0447 0.0447 4.0 1.30993 1.2646

0.004 0.0632 0.0632 10.0 1.5191 1.4289

0.01 0.0998 0.0998 30.0 1.6514 1.5202

0.2 0.4330 0.4328 60.0 1.6902 1.5451

0.8 0.7947 0.7910 100.0 1.7066 1.5552

From Table 20.1 it follows that the accuracy of the approximate (24) is higher for the smaller values of the Biot number Bi. Temperature distribution in the second heat transfer phase is calculated from (21) by accounting for (23). Example 2

rlx=o =101(1),

102 = o. (26)

596


This case is a good example of an ideal thermal shock on a unilaterally insulated flat wall surface. Temperature distribution in the first heat transfer phase is obtained from (10) by accounting for (26)

11=

Tol (t)(I-

~)2 ,

0~x~8,

(27)

8~x~L.

(28)

u

0,

From the heat balance (13), the following differential equation is obtained

ss 2 --=6aToI dToI (t ) . Tol () t 8-+8 dt dt By substituting tion

z= 8

2

(29)

into (29), one reduces it to a linear differential equa-

dz dToI (t ) . Tol ( t ) -+2z--=12Tol dt dt

(30)

It is easy to solve this equation by means of the integrating factor. The solution of (30), when initial conditions are 8!r=o = 0, has the form

(31)

where

p=

2

dToI (t)

Tol (t)

dt

(32)

When surface temperature is defined by function (33) then, by substituting (33) into (32), the following is obtained from (31): z =82

= 12at . 2m+l

(34)


597

For different values of m, we have

J=

3.464~,

m=O,

2~,

m=l,

1.549~,

m = 2,

1.309~,

m=3.

Due to the application of the Biot method, one has J

(35)

= 3.36~

for m

=0

and J = 2.29~ for m = 1. In the second heat transfer phase, the temperature field assumes the following form, once we account for conditions (26) in (18)

F01 ~Fo.

(36)

When all mathematical operations, which resemble those in example 1, are carried out, the following is obtained for m = 1

1

2

1)

_ CL [17 u--r O - - - (17 r O l - - e-3(FO-FOI)]

2

a

2

'

(37)

2

where F0 1 = at/L • Time t 1 is determined from (34) for m = 1 once we substitute J =L. The Fourier number F01 is of 0.25. Temperature distribution in the second heat transfer phase can be also easily determined for m = 0, 2, ..., n. Plate temperature distribution for the first and second heat transfer phase, for m = 1 is presented in Fig. 20.2 and 20.3. 12,0

I+---I--__ _--I--...f...-----I

T~50 10.0

~~-__I_--I--...f...-----I

8.0

1r-----fII~_+_--I--...f...-----I

4,0 ~--+~

()

0,4

0,6

0,8 xIL],O

Fig. 20.2. Temperature distribution in a flat wall; dependence on the Fourier number Fo = in the first heat transfer phase (Example 2), T = I:a/(CL2 )

ian:

598


10,0

T~10 8,0

6,0

~--+--+--~--+------4

4,0

°

0,2

0,4

0,6

0,8

x/L

1,0

Fig. 20.3. Temperature distribution in a flat wall; dependence on the Fourier number Fo

=at/L\ T* = Tna/(CL

2

in the second heat transfer phase.

)

Example 3

Temperature distribution in the first heat transfer phase is obtained from (10) by accounting for (38) first

t: =

40 (/)8 (1- ~)2 , 5 {0, 2

(39) 5~x~L.

Equation (13), once (38) is accounted for, assumes the following form:

~ [qO (t)02J = baq« (t).

(40)

The solution of (40), when initial condition is 8t=o = 0, is function 1/2

1

t.

0=& [ 40(t)!qo(t)dt ] ,

(41)

which yields, once we account for (38)

O=~ 6at

n+l

.

(42)


599

In the second heat transfer phase, temperature distribution is expressed as. t; =

40 (t)L (1-~J2 +u 2A

L

(43)

'

Once we account for conditions (38) in (18) and integrate the equation when the initial condition is ut=t l =0, we have

u(t)=

40 (t)L (2FO -IJ+ 40 (ll )L ( I _ 2FOIJ, 2A

n+l

2A

(44)

n+l

where time I} , determined from (42) once 8= L is substituted, is I} = (n+ 2 I)L /6a. Example 4

102 = 0,

(45)

The first heat transfer phase is described by formulas that are identical to the ones used in Example 1. In the second phase, temperature distribution is expressed by (16), which, once we account for (45), assumes the form 7'

111

=

Bi 1Toi + Bi-u + 2u Bi + 2

+

2Bi1u + Bi.Bi-u- 2Bi iToI x Bi l + 2

+ BilToI - BilBi2u - Bi 2u - Bi1u (~J2 Bi l +2 L

,

-+ L

(46)

When (18) is integrated, while (45) is accounted for when initial condition =0, one has is

«l..

(47) where 2

12( Bi l + Bi2 + Bi 1Bi2 )

f.1 = 12 + 4Bi1 + Bi1Bi2 + 4Bi2

(48)

Equation (48) is the approximation of the first root of characteristic equation

600


Ii Bl 2

Bi1)-1 . Bl 2

Bi1( Ii

ctgli=-. - - 1+-.

(49)

Table 20.2 displays the values of root Ii calculated from (48) for the selected values Bi, and Bi2• Table 20.2. Values of f.1 calculated from (48)

0.002 0.5 1.0 10.0

0.0632 0.6564 0.8675 1.5206

0.6564 0.9608 1.1390 1.7755

0.8675 1.1390 1.3093 1.9540

1.5206 1.7755 1.9540 2.7386

In all the analyzed cases, the analytical formulas have a relatively simple form. Moreover, it is not necessary to determine the roots of characteristic equations.

Exercise 20.3 Determining Thermal Stresses in a Flat Wall Determine thermal stresses in a flat wall caused by the temperature difference across the wall thickness. Next, calculate thermal stresses on the plate front face, which is L = 0.06 m thick. Temperature of the plate, which at an initial moment is zero degrees, increases on the front surface to TOl = 100 cC. Back surface is thermally insulated. Calculate stresses, which occur in the dimensionless time when Fo = 0.0075, assuming that thermophysical properties of the steel K18, from which the plate is made of, are 5 as follow: thermal expansion coefficient f3 = 1.2.10- 11K, longitudinal 4 elasticity modulus E = 19.13.10 MPa, Poisson ratio V= 0.3 and thermal 5 2 diffusivity coefficient a = }J(ep) = 1.325·10- m /s.

Solution Thermal stresses in the flat wall caused by a temperature drop across the wall thickness (in the direction of x axis) are expressed as (j

= (jyy () x = (jzz () x =-1- (NT -- + 12M3 Tx - E f3T J, I-v

L

L

where ayy and azz are normal stresses in the direction of y axis and respectively. Force NT and moment M Thave the form

(1)

z axis,

Exercise 20.3 Determining Thermal Stresses in a Flat Wall L

L

Nr =EpfT(x)dx,

Mr =EpfXT(x)dx.

o

o

601

(2)

If the plate ends are able to lengthen, but not able to bend, one should assume that MT = 0 and NT 0 in (1); if, however, it is not possible for the plate to lengthen or bend, then M T =0 and NT =O. When the wall of a cylindrical tank with a large diameter is treated as a flat wall, then one assumes that M T = 0 and NT "* 0 in (1). In this case, (1) assumes the form

"*

(J"=

Ep [T{t)-T{x,t)J.

(3)

I-v

Because in the first heat transfer phase TI = 0 for t5 ~ x ~ age temperature ~ is determined in the following way: -

1

1L

(J

L

11 =- f1l (x,t)dx =- f1l(x,t)dx+ f1l(x,t)dx Lo L 0 J

L, therefore, aver-

J=-1 Jf1l(x,t)dx. Lo

(4)

Once reference temperature is assumed Tod ' thermal stresses in the first heat transfer phase will be presented in the dimensionless form *

CTI =

1[1 f

CT{I-v) = - - J 1I{x,t)dx-1I{x,t) EPTod t: L 0 * CTI =

CT{I-v) E pt;

1 1J

=- -

t; L

f11 {x,t)dx,

],

O~x~t5,

t5~x~L.

(5)

(6)

0

In the second heat transfer phase, thermal stresses are given by *

CTn =

CT (1- v) =1- [ Tn - .: x i 1

Fig. 22.1. Shape functions N2 - i N/ for node i that lies on the boundary of elements (i-I) and i

The local numeration of node i in the global coordinate system is number (2). The first term on the left-hand-side is obtained by multiplying the second row in the capacity matrix (15) by the vector of derivatives with respect to time from node temperatures, i.e.

664

22 Solving TransientHeat Conduction Problems

cp

2a~~-I N~-Idx :H = cp

Nt

l

N~-I ,( N~-I

rJdx{;:~: }

=

[1, 2]{7;~I} = CPl'J.x (7;-1 + 27; ). 61 ;6

=Cp( Xi -

(4)

i- 1

Xi-I)

The second component on the left-hand-side of (3) can be calculated in a similar way:

(5)

The third term on the left-hand-side is obtained by multiplying the second row in the rigidity matrix [K e]

=A

[1 -1]

L -1

(6)

1

for a one-dimensional element by the temperature vector in the nodes of element (i-I)

a

2r i I -

z-r

-A J~N2 Xi

A

dx=t- I [- I, 1]

{1;-I} A T = 1'J.x0_ (-1;-1+1;).

X i _ I "

(7)

I

The fourth term on the left-hand-side is obtained as a result of multiplying the first row vector in the stiffness matrix [K e ] formulated in (6) by the temperature vector in nodes of element i (8)

where At i- I = Xi

-

Xi-I'

At i = X i+I -

Xi"

Accounting that vector {f;} for a one-

dimensional element and linear shape functions has the form

{f&} = 4;L

{a

the terms on theright-hand-side can be expressed as follow:

(9)

Exercise 22.2 Concentrated (Lumped) Thermal Finite Element Capacity

665

a) T

Til

i

I I , ..----.,

I 1 .... - - - - - - , I I

18xi-1

18xj

Xi~~l

b)

x

Xhl

1+3

i+4

i+6

c) f--~I,j+l

i,j+1 (4)

CD i·~-l,j

1+1,}+1

(3) (4)

(3)

CD

(1)

(2)

0)

(2)

(4)

(3) (4)

(3)

i+l,j

i.]

CD (1)

j---I,ll

CD (2)

0)

i,j-J

r» \.4./ i+1,l-·-1

Fig. 22.2. Diagrams that illustrate the concentration of thermal capacity in node i of a) one-dimensional elements, b) two-dimensional triangular elements, c) twodimensional tetragonal elements

666

22 Solving Transient Heat Conduction Problems

Xfi .

qv

N i - 1d 2

X

+

Xif+l. Nid _

qv

Xi

Xi-l

1 X -

qv Axi- 1 +q.Sx, -· 2

2

(10)

By accounting for (4), (5), (7), (8) and (10) in (3) one has

(11)

For equal element lengths, when Ax;-l = Ax; = Ax, (11) can be written in the form CPAx(~

6

1i-l

~ )_ 1 1;-1 -21; +1;+1 _ . A ..,. + 4~ i , + 1i+l /l" - qvD.A .

Ax

(12)

From the analysis of (12) it follows that the derivatives after time from temperatures in three nodes appear on the left-hand-side of the equation. Nodes (i-I) and (i+ 1) located next to node i, which has the largest weight equal to 4/6, weigh 1/6. Thermal capacity concentration (lumping) is based on the assumption that the temperature change rate in all three nodes is equal (Fig. 22.2a), i.e. (13)

By accounting for this assumption in (12), one has (14) Identical equation is obtained when the straight line method, characterized by a very good accuracy, is applied. If we assume that temperature change rates in all element nodes are identical, then the forms of thermal capacity matrixes are simplified as follow: • one-dimensional element (15)

• triangular element

Exercise 22.2 Concentrated (Lumped) Thermal Finite Element Capacity

1 p e e [M ]=C: 0

0

0

0

667

0

1 0

(16)

1

• tetragonal element 1 0 0 0

[Me] = C~Ae

0

1 0 0

0

0

1 0

0

0

0

(17)

1

In each of the elements with common node i , one can single out a region with constant temperature change rate ~e that can be subsequently used to calculate heat accumulation. In the case of a one-dimensional elee/2. ment, the length of the region measures L For a triangular element, the e/3, surface area is A while in the case of the tetragonal element, the surface e/4 area is A (Fig. 22.2). In the global equation system for the entire region, in the equation for node i, a term appears on the left-hand-side of the equation that describes thermal changes in time of the heat accumulated within the region that can be assigned to node i. In the case of a one-dimensional problem, such region measures in width (1h;_/2 + 1h/2). If node i is surrounded by triangular elements (Fig. 22.2b), then temperature change rate Ne

d'I', /dt in region 1/3

LA)

is equal. Symbol Ne stands for the number of

)=1

triangular elements, which share common node i. In a case when the region is divided into tetragonal elements, the region with an equal temperature change rate is formed by summing up 1/4 of the elements surface area with common node i (Fig. 22.2c). It is evident, therefore, that the change in heat quantity Qok in time within the control volume, whose surface is Ne

1/4

L A) is expressed as(Fig. 22.2c) )=1

dQok dt

=! I, A'cp dT; . 4

)=1

(18)

dt

One should add that the procedure in the finite volume method (control) is identical to the procedure discussed above, as one assumes that temperature change rate is constant within the entire control volume and equals d'T[dt, where i is the node that lies inside the finite volume and is assigned to this volume. Concentrating thermal capacity of a control area in a single node has its advantages; it facilitates calculations and enables one to

668


integrate the global system of ordinary differential equations, which define temperatures in element nodes with a larger time step I1t. Thermal capacity concentration does not decrease the accuracy of FEM, but rather it increases calculation stability.

Exercise 22.3 Methods for Integrating Ordinary Differential Equations with Respect to Time Used in FEM Describe basic integration methods for a global ordinary differential equation system with respect to time. Such system is obtained in a semidiscrete FEM by dividing a region into finite elements.

Solution If a differential equation system is known for an individual element (16) presented in Ex. 22.1, one can create a global equation system the way it is described in Ex.ll.15. Global ordinary differential equation system for node temperature has the form (1)

MT+KT=F, where, N

M=[M]= I[ Me],

(2)

e=l

N

K

= [K] = I([ K:

J+[K~ J),

(3)

e=l

F = {fQ} + {h} + {fa}

. [. .r

T=

11, ..., TN

T = [11,

..., TN

,

(4)

,

(5)

r'

(6)

where N is the node number in the entire analyzed region. Capacity matrix [Me] is discussed in Ex. 22.1 and Ex. 22.2, while stiffe e ness matrixes [K c ] and [K a ] and vectors lfQ } , ~} and lfa} are determined for different elements and boundary conditions in Ex. 11.11-11.15. A generalized Crank-Nicolson method, also known as () method, will be applied to numerically integrate the equation system.

Exercise 22.3 Methods for Integrating Ordinary Differential Equations

Between the temperatures in time t lowing relation occurs

n 1

+

and t"

669

= ntst, n = 0, 1, ... the fol-

r+! = r- +[ (1- e) t + et n+! ]!'1t , n

(7)

where 0 ~ ()~ 1. Equation (7) is known as a generalized trapezoidal approximation. The n 1 global equation system (1) will be written for t + and t" first (8) (9)

The first equation system should be multiplied on both sides by (), while the second by (1- ())

e( Mt 1+Kr+ 1)=eF 1, n+

n+

(10)

(11) By adding the sides of (10) and (11), one has

M[(l-e)t +et n+!]+K[(1-e)r +er+1]=(1-e)F +eF 1, n

n

n+

(12)

while after allowing for (7), the equation has the form

As a result of simple transformations of (13), one has

(~t M+eK)r+1=[~t M -(1-e)K Jr +(l-e)F

n

+eF 1. n+

(14)

If () ~ 1/2, then the solution stability is ensured for the arbitrary time step I1t. However, time step I1t should be small due to the accuracy of temperature determination. Depending on the value of parameter () , the following methods are obtained: ()=

0

1/2 ()= 2/3 ()= 1

()=

- explicit method; it is stable under the condition that time step I1t is smaller than the reliable boundary value, -Crank-Nicolson method, which is unconditionally stable, - Galerkin method, which is unconditionally stable, - implicit method, which is unconditionally stable.

670


Explicit method (() = 0) ensures high calculation accuracy with a small time step. The smaller the quotient Aela is, the smaller the time step should be. The accuracy order of the explicit method is 1, i.e. O(~t). It is very n l easy to determine temperatures in nodes T + by means of the formula obtained from (14) with () = 0

r+1=r +M(M-1Fn -M-1Kr)

(15)

when matrix M is diagonal due to the concentration (lumping) of the elements thermal capacity, and when it is easy to determine the inverse matrix 1 M- . Despite the limitations of the time step I1t, the explicit method is frequently used, since it is very accurate for a small time steps, especially when the temperature change rate for a solid is high. From the calculations in Chapter 21, one can conclude that the explicit method is no less accurate than the implicit method (() = 1) when the time step ~t is the same for both methods. The advantage of the explicit method is that Tn+1can be easily determined, since there is no need to solve the equation system for every time step when matrix M is diagonal. Implicit method does not have this advantage, when () = 1. In the implicit method, the linear algebraic equation system must be solved at every time step by means of the direct methods, such as for e.g. Gaussian elimination method or by iterative methods, such as for example Gauss-Seidel method or over-relaxation method (SOR). The examples of solving the equation system with the implicit method are presented in Chap. 21. Crank-Nicolson method (()= 1/2) has the second order of accuracy, i.e. O[(~t2)] and is unconditionally stable. If, however, the time step ~t is too large, then the solution becomes less accurate and exhibits oscillations, which do not occur in reality. As in the case of the implicit method, the linear algebraic equation system must be solved for every time step. Aside from the basic algorithms discussed above, which are used to solve the ordinary differential equation system, many other effective algorithms can be applied, for example. Rung-Kutt method or the algorithms of the prediction-correction type.

Exercise 22.4 Comparison of FEM Based on Galerkin Method...

671

Exercise 22.4 Comparison of FEM Based on Galerkin Method and Heat Balance Method with Finite Volume Method Compare different methods used for solving equations, which describe heat conduction in a flowing fluid or in a solid that flows at a velocity of wx =U

a ax

2 et et T qv - + u - = a -2 + - . cp

at

ax

(1)

Carry out the discretization of (1) for an internal node by means of • FEM based on Galerkin method, • integral heat balance method discussed in Chap. 20, • finite volume method (finite difference method). Also discuss thermal capacity concentration (lumping) of an element in FEM and integral heat balance method. Finite element mesh is nonuniform.

Solution First, (1) will be discretisized by means of FEM based on the Galerkin method [7] as it is done in Ex. 17.2. Once Galerkin method is applied, (1) is approximated according to FEM by means of equation

(2)

=

Xi

Xi+l

Xi-l

Xi

fqvN~-1 dx + fqvNfdx.

Accounting that shape functions -1 _

N 2i

X - Xi-1

-

_

, Xi -Xi-1

N; and N;-l have the form i N1 -

Xi+1-X

(3)

Xi+1- Xi

and that temperature distribution in elements i-I and i (Fig. 22.3a) is described by (1) and (2) from Ex. 22.2, from (2) one has

672


(4)

where a = }J(ep). If nodes i are evenly spaced out, (4) has the form ..) U 1;-1 - 21; + 1;+1 Ax ( . 1;-1 +41; +1;+1 +-(1;+l-1;-l)-a 6 2 Ax

-

qv

= Ax- . cp

(5)

Next, equations will be derived by means of FEM based on the heat balance method, which was thoroughly discussed in Chap. 20. a) T

~Xi-I

= Xj-Xi_l

~Xi=Xi+1 -Xi

I

O---~

,- -

""I

NI-.. I , I

T

II

i-I

I I

II~,

I I

I I

/II@,

r,

"

CD

I I ~.i

"

I,,~l'vi

I " I "" -,

Fig. 22.3. Approximation of a one-dimensional transient temperature field at a selected moment t: a) FEM, b) finite volume method

Exercise 22.4 Comparison of FEM Based on Galerkin Method...

673

Accounting that temperature distribution between the nodes is approximated by a straight line by means of (1) and (2) from Ex. 22.2, the heat balance equation has the form ari-1

Xi

Xi+l

er

ar i-1

Xi

Xi+l

er

cp f--dx+Cp f-dx+cpu f--dx+cpu f-dxat

Xi-l

Xi

at

ax

Xi-l

ax

Xi

(6)

Once mathematical operations are carried out, the following results are obtained:

(7)

Xi-

In a case when the finite element mesh is uniform, when l = At, (7) has the form ~(

-

8

.

..)

U

7;-1 + 67; + 7;+1 + -(7;+1 - 7;-1) - a 2

X i+ l -

7;-1 - 27; + 7;+1 qv = ~- . Ax cp

Xi

=

Xi -

(8)

In the finite (control) volume method (Fig. 22.3b), the equality of temperature change rate is assumed for nodes (i - 1), i and (i + 1), i.e. d7;-1

at:

d7;+1

dt

dt

dt

(9)

--=-=--

By accounting for (9) in (7), one has

U(T

T) +a (7; -7;-1 + 7; -7;+1)_-

Xi+1- Xi-1 T ---.Ii+-.Ii+1-.Ii-1

2

2

2

Xi -Xi-1

Xi+1 -Xi

(10)

cp

If the mesh is uniform, then (10) assumes the form A ...... ( LU

)Tt , +-U (T.Ii+1-.Ii-1 T) -a 7;-1 2

27; + 7;+1 _

qv

~

cp

A ...... -LU-.

(11)

674


Identical equation is obtained by means of the finite difference method, 2 if derivatives aT/ax and a 2T/ax are approximated by central difference quotients. From the comparison of (5), (8) and (11) one can conclude that weight coefficients with i; are, respectively 4/6, 6/8 and 1. One can see that the smallest coefficient occurs in the Galerkin-based FEM, a slightly larger one in the FEM based on the integral balance method, while the largest one in the control volume method (of finite differences). It is easiest to solve the equations obtained from the control volume method (11) by means of the numerical methods. The solution of the equation system (11) for all nodes enables one to accurately determine temperature distribution (Chaps. 21, 23).

Exercise 22.5 Natural Coordinate System for One-Dimensional, Two-Dimensional Triangular and Two-Dimensional Rectangular Elements Discuss the natural coordinate system for one-dimensional elements and two-dimensional triangular and rectangular elements and linear shape functions in the natural coordinate system.

Solution a. One-dimensional elements In the local coordinate system (Fig. 22.4), one-dimensional temperature distribution is described by function

T" =(1-

~) Tie + ~ t: = »tt: + N~Tz" =[ Ni N~ ] { ~: } . 2

Fig. 22.4. Linear approximation of temperature distribution in the element e

(1)

Exercise 22.5 Natural Coordinate System for One-Dimensional

675

Once local dimensionless coordinate system is introduced (Fig. 22.5) j:

';,

= 2:X -1 L

(2)

'

the coordinate for node 1 is ; = -1, while the coordinate for node 2 is ;= 1. Accounting for (2) in (1), one has

T"

=~(1- ~nl1e +~(1 + q)Tz" =stt: + N~T{ =[NtN~J{~:}.

(3)

where,

N\e =~(l-q),

(4)

N~ =!(l+q)

(5)

2

are linear shape functions. One should note that local coordinate formula

:x

can be expressed by means of

(6)

Thus, (3) and (6) are very similar in form. ~=-1

~=1

L

Fig. 22.5. Local dimensionless coordinate system (natural coordinate system)

b. Two-dimensional tetragonal elements Local dimensional and dimensionless coordinate systems (natural) are presented in Fig. 22.6. If natural coordinates are introduced -

x

y-

q = b - 1 and 17 = ~ - 1,

(7)

then linear shape functions, described by (19) in Ex. 11.9, assume the following form:

676


YJ YJ=l

2a

~

~=1

0

o

yJ

~

b

=-1

2b

x-

Fig. 22.6. Local (x,y) and natural (;,17)coordinate systems

Nt =±(1-;)(1-17), N 2 =~(1+;)(1-17), 4

(8)

1

N; =- (1 + ~) (1+ 17 ), 4

N 4 =!(1-;)(1+17).

4

c. Two-dimensional triangular elements Linear shape functions for a triangular element are defined by (7) in Ex. 11.9. Natural (area) coordinate system is presented in Fig. 22.7. By connecting point P = P(x, y) with the vertices of triangle 123, three smaller triangles are obtained whose surface areas are AI' A 2 and A 3 (Fig. 22.7). Natural coordinate system (~,17,') is defined as follows: L1 =;

Al

=7 ' A2

L2

=17=7' A3

L3 =s=7'

where A

e

=Al + A

2

+ A 3 is the area of the whole triangle 123 (Fig. 22.7).

(9)

Exercise 22.5 Natural Coordinate System for One-Dimensional

677

y

7 ~o

.

o

.x

Fig. 22.7. Natural (area) coordinate system

Only two of the natural coordinates ;,1],;are linearly independent, since Al

A2

A3

A

A

A

A

A

e

-+-+-=-=1=;+1]+; . e e e e From (10) it follows that coordinate functions ; and 1]

(10)

s: for example, can be expressed by

;=1-;-1].

(11)

All three natural coordinates change at interval [0,1]. If point P, which lies inside the element, is moved to node 1, then Al = At23 (Fig. 22.7) and natural coordinates equal; = 1, 17 =0 and S=o. If point P becomes identical with point Q, which shifts along side 23, then Al = 0, A 2 *- 0, A 3 *- 0 and the respective natural coordinates are ~ = 0, 1] *- 0 and;*- O. Similarly, when point P becomes identical with point M, which shifts along side 13, then the natural coordinates are ~ *- 0, 17 = 0 and;*- O. If shape functions that interpolate temperature distribution inside the element are linear, then

N1e =L1 =;, N~

=L 2 =1],

(12)

N; =L 3 =;. Between the natural coordinates ;, 1] and ; and global coordinates x, y and z the following relationships exist

678

22 Solving Transient Heat Conduction Problems X=~Xl

+17 X2 +SX3,

Y = ~ yl + 17 Y2 + SY3 ,

(13)

1 = ~ + 17+s. Once the equation system (13) is solved with respect to gets

~,

17 and S, one

(14)

where 2 At23 is defined by (5) in Chap. 11. Coefficients

u,

a;, a;, a;,

bt,

b;, c;, c; , c; are described by (8) in Chap. 11. The superscript e means that the quantities refer to a single element e. Natural coordinates are introduced with an aim to simplify the calculation of surface integrals by means of the Gauss-Legendre quadratures method. Only linear shape functions were analyzed. Analogically, the same procedure applies in the case of higher degree shape functions, for example quadratic or cubic [12, 21]. Exercise 22.6 Coordinate System Transformations and Integral Calculations by Means of the Gauss-Legendre Quadratures Discuss the transformation of coordinate systems for arbitrarily-shaped tetragonal and triangular elements and the calculation of integrals by means of the Gauss-Legendre quadratures.

Solution In Chap. 11, the integrals that occur in the coefficients of conduction matrixes and also other integrals of an algebraic equation for i-node are analytically calculated. This is possible for rectangular or triangular elements. If a region is divided into arbitrary quadrilaterals, then the analytical calculation of the integrals becomes rather problematic. In large commercial

Exercise 22.6 Coordinate System Transformations and Integral Calculations

679

programs, integrals are usually calculated numerically by means of the Gauss-Legendre quadratures. For this purpose, an arbitrarily-chosen quadrilateral is transformed in the coordinate system (x,y) into the, so called, model element whose dimensions are 2 x 2 in the new coordinate system (~,1]). The model is a square: 1 S ~ S 1, 1 S 1] S 1. Coordinate transformations are only applied in order to calculate the integrals. The transformation of element B is shown in Fig. 22.8. After the transformation of coordinates (x,y), the elements of integration in the new coordinate system (~,17) become more complex; in effect, therefore, a numerical method, usually the Gauss-Legendre method, is applied to calculate these integrals. The real element B in the system (x,y) is transformed into the model element in the system (~, 17) by means of the transformation m

x= LxjNj(~,17), j=l

(1) m

y = LyjNj (~,17), j=l

where ~e(~,17) is the shape function in the model element. The examples of such transformation are (6) and (13) in Ex. 22.5.

1] = 1

4

3

"L;

;=-1

; =

1

B

--

17 =-1

2

/ /

Fig. 22.8. Transformation of an arbitrary tetragonal element B in the Cartesian coordinate system (x,y) into a quadratic model element in the coordinate system (;,1])

680


Temperature distribution in element e is expressed as n

:=Te(x,y)= IrtN;(x,y),

t:

(2)

j=l

where n is the number of nodes in element e. Natural number m , which occurs in (1) does not have to be equal to number n in (2). Depending on the relations between m and n, the elements can be divided into

• subparametric (m < n), approximation order of coordinates x and y is lower than the approximation order of temperature (in the general case of a dependent variable), • isoparametric (m = n), approximation orders of coordinates x and y and temperature are identical, • superparametric (m > n), approximation order of coordinates x and y is higher than the approximation order of temperature. Most frequently, the isoparametric elements are used, for which m = n. Next, the transformation of coordinates will be discussed in greater detail. The quantities, which should be transformed are

) N je(X,y,

aN; -,

aN;-

ax

drA= dxdy.

and

8y

(3)

They occur in integrals, which result from the application of FEM. For instance, the coefficients of conduction matrixes K;,ij ((26), Chap. 11) are formulated as follow:

e

e

x:.. = f(A aN )dXdY . aX aN; aX + AaN aY aN; rl., sr vy i

c,l)

i

Y

x

(4)

N;

It is easy to express quantity (x, y) in functions ~ and 17 once the (1) is allowed for. The derivatives from the shape function are calculated in the following way:

aNt aNie ax aNie ay

--=----+---a~ ax a~ 8y a~'

aNe aNe ax aNt ay i

i

--=----+----. a'7 ax a17 8y a17 Equations (5) and (6) can be written in the matrix form

(5)

(6)

Exercise 22.6 Coordinate System Transformations andIntegral Calculations

aN a; aN a1]

e i

e i

681

ax ay aNt a; a; ax = ax 8y aN a1] a1] ay

(7)

e i

where the square matrix with dimensions 2x2 is a Jacobian determinant

J=

ax 8y a; a; ax 8y a1] a1]

(8)

The transformation of coordinates is unique when the Jacobian J is not singular, i.e. when Jacobian determinant is other than zero at every point (;,1])

ax ay ax a; a1] a1] a;

8y J=detJ=------:;t:O.

(9)

Derivatives from integral (4) are determined from the transformation of (7)

aN aNt -a; ax -l-'l' aN aN ay a1]

e i

e i

e i

(10)

The required derivatives for the calculation of the Jacobian determinant (9) are obtained after the differentiation of

(11)

(12)

682


The element of surface area dxdy equals

dxdy = det Jd~d17.

(13)

From (10) or directly from the solution of the equation systems (5) and (6), one has

1_[

e

aNi _ _ By aN; _ By aN;] ax - detJ a17 a~ a~ a17 '

(14)

(15)

Integral (4) can be transformed into a new coordinate system when the derived relationships are applied. The first component of this integral can be transformed by means of the (13)-(15) into a form

r

=

J(AX aN;" aN; )dXdY=

sr

ax ax

(16)

One can see, therefore, that after the transformation of coordinates, the subintegral expressions are more complex in the new coordinate system (;, '7) than they are in the coordinate system (x, y). These integrals are usually numerically calculated using the Gauss-Legendre quadrature [1, 3, 1117,21]. If the subintegral function is denoted by F(~,17), one can calculate the integrals in the new coordinate system by means of a relatively simple formulas.

a. One-dimensional elements The integral is calculated by means of formula 1

n

1= JF(;)d;= LW;F(;i)' -1

(17)

i=1

where ~i are the Gaussian point coordinates (Fig. 22.9). Coordinates ~ are the zeros of Legendre polynomials [13]. Coordinates ~ and weights Wi' which occur in (17) are compiled in Table 22.1.


-0,577350

683

0 577350

-1

b)

-0 774597

0774597

-1 Fig. 22.9. The location of Gaussian points during the calculation of a onedimensional integral: a) n =2, b) n =3

Table 22.1. Legendre polynomials and the coefficients of the Gauss-Legendre quadratures ~>_~~_~~Ees-SL~ 1 0,0 2 ±0,577350 3 0,0 ±0,774597 4 ±0,339982 ±0,861136 5 0,0 ±0,538469

_

Weight coefficients 2,0 1,0 8/9 =0,888 . 5/9 =0,555 . 0,652145 0,347855 0,568889 0,478629 0,236927

Wi

The integration by means of the Gaussian quadratures yields accurate results for n integration points, when F( ~ is the polynomial of degree 2n-1 or lower. In general, the larger the number of Gaussian points n, the more accurate the calculation of integral (17) is. Now we will discuss the approximate calculation of two-dimensional integrals for tetragonal and triangular elements.

684


b. Tetragonal elements Formulas for the calculation of an integral in a two-dimensional region are used to determine integrals for quadrilateral elements.

11

1[

1= IlF(~'17)d~d17=l ~WjF(~h17) d17= n

]

(18)

=~Wk[~WjF(~h17k)]= ~~WjWkF(~h17k)'

where n is the Gaussian point number in a single direction. For n = 2, the integral (18) can be written as follows:

= Wlw1F(;1 ,'71) + W1 w2F( ;1,'72) + W2 w1F(;2 ,'71) + W2 w2F( ;2,'72),

I

where the coordinates of Gaussian point are ~, '7i = ±1/3 wt z = wtW Z =W zz = 1.

t12

(19)

= ±O.57735 and

Table 22.2. Calculating integrals in a quadrilateral region by means of (20)

m i

1

1

0

o

4

1 2 3 4

_1/31/2 +1/31/2 _1/31/2 +1/31/2

_1/31/2 _1/31/2 +1/31/2 +1/31/2

4

'YJ = 0.577 .......

'YJ =-0.577 ... I

~=-0.577 ...

9

1 2 3 4 5 6

_(3/5)1/2 0 +(3/5Y/2 _(3/5)1/2 0 +(3/5)1/2

7

_(3/5)1/2

8 9

0

_(3/5)1/2 _(3/5)1/2 _(3/5)1/2 0 0 0

7, 'YJ = 0.774... -

\

~ = 0.774 ...


685

One can see, therefore, that once the numeration of nodes i = j + (k - l)n is introduced, the integral (18) can be written in the form m

1= IF(;i,17i)Wi

,

(20)

i=l

n. = a k and w.1 = w.w • Quantities a. and w. denote cowhere m = n', '='1J:. = a., k ) '/1 } } } ordinates ~ and weights Wi' respectively, compiled in Table 22.2 and are used to calculate two-dimensional integrals.

c. Triangular elements To calculate the integral, coordinates (x,y) are transformed into area coordinates L} and L2 , which are linearly independent, since once we account for the (11) from Ex. 22.5, coordinate L 3 can be calculated from formula

L3 = 1- L1 - L2 • By allowing for equation

aNt ax aNie ay

=[Jr

aNie aLl aNie aL2

(21)

where

ax aLl 8x aL2 -

[J] =

ay

u. 8y 8L2

(22)

surface integral I for a triangular element is calculated from formula 1

1=

1-~

JJF(LJ,L

o

0

m 2,L3

)d~dLl ~ LF(Ll,i,L2,i,L3,i )Wi

(23)

i=l

The locations of integration points and weight coefficients for the triangular element [1, 3, 11, 12, 14, 15, 21] are compiled in Table 22.3. In both, Chap. 11 and this chapter, the discussion was limited to one and two-dimensional steady-state and transient heat conduction problems. Three-dimensional problems are solved analogically, in keeping with the rules that were applied in the examples of two-dimensional problems, which were discussed above.

686


Table 22.3. The location of integration and weight points for a triangular element

Integration points Point location number

Error

. tCoordinatesWeights POln L 1, L 2, L 3 Wi

1

1

1

-, -, 333

a

~2' ~2' °

c

°~ ~ ~ °~

3

a

1

3 1

, 2' 2

3

2' , 2

3

1 1 1 3' 3' "3

1

27 48

0,6; 0,2; o,2)

25 0,2; 0,6; 0,2 48

4 d

0,2; 0,2; 0,6

a

3' 3' 3

b

7 e f g

1

1

1

0,2250000000

/31 /31) /31 0,1323941527 /31 /31 al

al /31

al

/32, /32) /32, o., j32 0,1259391805

a-,

j32, j32, a,

Constants at' a 2, PI and 132 are a 1 = 0.059715871 7, PI = 0.4701420641, =0.7974269853, =0.1012865073.

Exercise 22.7 Calculating Temperature in a Complex-Shape Fin by Means

687

Exercise 22.7 Calculating Temperature in a ComplexShape Fin by Means of the ANSVS Program Oval pipes with an attached aluminum plate-fins, l\ = 0.08 mm thick are used in car radiators [19]. Due to the division of plate-fin into fictions (equivalent) fins, temperature distribution in the entire lamella can be determined when temperature distribution only in half of the fin is analyzed [19]. The maximum length of the pipe diameter is dm ax = 11.82 mm, while the minimum =6.35 mm (Fig. 22.10). The height of the fin half section is h =9.25 mm, while the width s = 17.0 mm. Initial temperature of the fin is To = 20°C. The temperature of surroundings is also Tcz = 20°C. At an instant t = 0 s , the fin base temperature increases by a step from temperature To = 20°C to Tp = 95°C.

«:

ANSYS

Fig. 22.10. The division of 1/4 of a plate-fin into finite elements Determine transient fin temperature distribution at time t 1 = 1.0 sand t 1 = 0.2 s and temperature transient in the upper-left fin corner in the function 2·K). of time. Heat transfer coefficient on the fin surface is a = 75 W/(m Heat is given off by the fin to surroundings through the lateral surfaces and through the left lateral front face. The upper and right-hand-side surfaces are thermally insulated. Straight sections of the fin base are also thermally insulated due to the symmetry of the temperature field with respect to the

688


Al·r~r:ts 5. 5 • 3 AUG 1 2001 18:27:13

NODAL SOLUTION STEP=1 SUB =1 !Dr

TItIE=l TEMP SMN =78.598 SI!X =95 A =79.0509 B =81.331 =83.154 C =84.976 D =86.799 E F =88.621 G =90.444 =92.266 H =94.089 I

Lame La 2

.li..NSYS 5. 5 .3

P..UG 1 2001 19:43:38 lJODAL SOLUTION TIME=.2

TEI1P RSYS=O

(AVG)

Po'(verGraphics EFACET=l AVRE:3=Mat SHN" =40.551 SHX =95 A. =43.576 B =49.626 C =55.676 D =61.726 =67.776 E =73.82.5 F =79.875 G =85.925 H =91.975 I

Fig. 22.11. Distribution of isotherms in a fin: a) t 1 = 1.0 s, b) t2 = 0.2 s

Exercise 22.7 Calculating Temperature in a Complex-Shape Fin by Means

688

horizontal axis of the pipe cross-section. The pipe axis is at a distance of 9 mm from the left side. Assume for the calculation that the aluminium has the following thermo-physical properties: A = 207 W/(m·K), C = 879 Jz(kg- K) and p = 2696 kg/m'.

Solution Due to the symmetry of the temperature field in the fin shown in Fig. 22.10, the temperature distribution will be determined only for one-half of the fin, which is in thickness Jz/2 = 0.04 mm. The back surface of the fin is thermally insulated, while the heat is given off to surroundings on the fin's front surface. A quarter of the conventional fin was divided into 1500 elements (Fig. 22.10). Temperature was determined in 3198 nodes. Only one finite element is located at 5/2 = 0.04 mm. Calculations were carried out by means of the ANSYS program. The isotherm history on the lateral fin surface at time t 1 = 1.0 s is presented in Fig. 22.11a, while at time t 2 = 0.2 s in Fig. 22.11b. It is evident that the fin quickly becomes heated and at an instant t, = 1.0 s temperature distribution is almost steady-state. Temperature history for the upper left-hand-corner of the fin (point MN in Fig. 22.11) is presented in Table 22.4 and in Fig. 22.12. Steady-state temperature at the point MN is TMN = 78.958°C. It is clear, therefore, that already after time t = 1.2 s temperature differs by Table 22.4. Temperature history for the upper left-hand-comer of the fin (point MN)

Entry no. 1 2 3 4 5 6 7 8 9 10

Time t 0.00 0.10 0.20 0.30 0.40 0.50 0.60 0.70 0.80 0.90

Temperature 20.00 23.78 40.55 54.85 63.93 69.55 73.03 75.18 76.50 77.59

Entry no. 11 12 13 14 15 16 17 18 19 20

Time t 1.00 1.10 1.20 1.30 1.40 1.50 1.60 1.70 1.80 1.90

Temperature 77.81 78.17 78.30 78.41 78.49 78.53 78.56 78.57 78.58 78.59

690


e = 78.304 - 78.598 .100 = -0.37% 78.598 From the steady-state temperature. Fin temperature quickly reaches the steady-state, since for the aluminum thermal diffusivity is very high and is a = }J(ep) = 207/(879·2696) = 8.735.10-5 m2/s.

J\NSYS

8,s

T1

eo 7f2

=:.

6.4

---J

-c::C

>

56

.4B

.40

'Jf2

2"'i

rs 0

TIME Lame La 2

Fig. 22.12. Temperature history in the upper left-hand-corner of a fin (point MN in Fig. 22.11)

Literature 1. Akin JE (1998) Finite Elements for Analysis and Design. Academic PressHarcourt Brace & Company, London 2. Anderson JD (1995) Computational Fluid Dynamics. The Basics with Applications. McGraw-Hill, New York 3. Bathe KJ (1996) Finite Element Procedures., Prentice Hall, Upper Saddle River 4. Burnett DS (1988) Finite Element Analysis. Addison-Wesley Publishing Company, Reading

Literature

691

5. Champion ER (1992) Finite Element Analysis in Manufacturing Engineering. McGraw-Hill, New York 6. Ergatoudis I, Irons BM, Zienkiewicz OC (1968) Curved isoparametric quadrilateral elements for finite element analysis. Int. J. of Solids and Structures 4: 31-42 7. Fletcher CAJ (1984) Computational Galerkin Methods. Springer, New York 8. Gresho PM, Sani RL, Engelman MS (2000) Incompressible Flow and the Finite Element Method. Wiley, Chichester 9. Irons BM (1966) Engineering Application of numerical integration in stiffness method. AIAA J. 4(11): 2035-2037 10. Lewis E, Ward JP (1991) Finite Element Method. Principles and Applications. Addison-Wesley, Wokingham 11. Logan DL (1997) A First Course in the Finite Element Method Using Algor. PWS Publishing Company, Boston 12. Moaveni S (1999) Finite Element Method. Theory and Applications with ANSYS. Prentice Hall, Upper Saddle River 13. Ralston A (1965) A First Course in Numerical Analysis. McGraw-Hill, New York 14. Reddy IN, Gartling DK (1994) The Finite Element Method in Heat Transfer and Fluid Dynamics. CRC Press, Boca Raton 15. Segerlind LJ (1984) Applied Finite Element Analysis. Wiley, New York 16. Stroud AH, Secrest D (1966) Gaussian Quadrature Formulas. Prentice Hall, Englewood Cliffs 17. Szmelter J (1980) Computer Programming Methods in Mechanical Engineering (in Polish). PWN, Warsaw 18. Taig IC (1961) Structural Analysis by the Matrix Displacement Method. English Electric Aviation Report SO17 19. Taler D (2002) Theoretical and experimental analysis of heat exchangers with extended surfaces. Ph.D. thesis, Univ. of Science and Technology 20. Taylor C, Hughes TG (1981) Finite Element Programming of the NavierStokes Equations. Pineridge Press Ltd, Swansea 21. Zienkiewicz OC, Taylor RL (2000) The Finite Element Method. Ed. 5. Butterworth-Heinemann, Oxford

23 Numerical-Analytical Methods

Numerical-analytical methods are based on the method of lines [14,28,31, 36-38], which underwent particularly intensive development at the beginning of 1970s [10, 11, 14, 15, 22, 26, 28, 31, 36-38]. These methods are also called semi-analytical or semi-numerical methods. The method of lines not only can be used for solving steady-state and transient heat conduction problems [16,41,42,48], but also for heat-flow problems [10, 11, 15, 22, 26, 28, 38, 40]. The method is also an effective tool for solving inverse transient heat conduction problems [13, 20, 25, 40, 43-45]. In numerical methods, only spatial derivatives are usually discretisized in the heat conduction equation. Due to the application of the control (finite) volume method to the heat conduction equation, one has (Chap. 11) p ( 1; ) c (1;) V;

~ = ~ x, [ t, (t)- 1; (t )] + qv (1;) V; ,

(1)

where (2)

Coefficient D y.. is, in general, a function of a distance l.y between nodes, a function of the surface area Sjj' through which the heat flows from node j to node i, while in the case of irregular meshes, in which the node-connecting straight line is not perpendicular to surface Sij' it is also a temperature function in nodes adjacent to nodes i and j. Symbol n is the number of control volumes, which share a common side with volume n. If thermo-physical properties A, c and p are temperature-independent, then K j coefficients are constants. Usually, the explicit or implicit Euler method or the Crank-Nicolson method, which will be briefly discussed, is used to integrate the ordinary differential equation system (1).

694


Explicit Method Derivative after time is approximated by the forward difference quotient

d1; ~ 1; (t + L\t) - 1; (t ) dt ~ L\t ·

(3)

By accounting for (3) in (1), one obtains (assuming that thermo-physical properties and qvare constant) the following expression, which makes it possible to determine temperature T, in all nodes at the new time point t +

L\t L\t[n n 1;(t+L\t)=-. IKijT;(t)+ [pc~ - - IKij 1;(t)+qv~ . ~ j=l L\t j=l

J

pc

.]

(4)

Implicit Method Derivative after time is approximated by a difference quotient (3), while the right side of (1) is calculated in the temperature function at time t + L\t

peV;

7; (t + ~t ) - 7; (t )

L\t

n . =IKij[T;(t+L1t)-T;(t+M)]+qvV;.

(5)

j=l

By transforming (5), one obtains

qvL\t -L\t. [[pc~ -+ ~ LJKij 1;(t+L\t)- ~ LJ Kij1j(t+L\t) =1;(t)+-. pc ~ L\t j=l j=l pc

J

]

(6)

Algebraic equation system (6) must be solved at every time step.

Crank-Nicolson Method Crank and Nicolson proposed [13] to approximate the right side of (1) using the arithmetic mean taken from the values calculated for t and t + I1t. Equation (1) is approximated as follows:

Exercise 23.1 Integration of the Ordinary Differential Equation System

pc V;

1; (1 + L11) - 1; (1)

L11

1{

=2

695

n

IKij[1j(t)-1i(t)J+ j=l

+~Kij[Tj(t+M)-1i(t+M)J}+qvV;.

(7)

Once (7) is transformed, the algebraic equation system is obtained; its form is as follows:

PCV 1 n ) 1 n IKij 1;(t+L1t)-- IKij1j(t+L1t)= ( -L1t+ 2 j=l 2 j=l PCV 1 n) 1 n qv = ( - - - IKij 1i(t)+-IKij1j(t)+-.. L1t 2 j=l 2 ]=1 pci',

(8)

In (1)-(8) Vi is the volume of a control area (control volume), while n is the number of control volumes j, which are adjacent to the analyzed volume i. Nodes are located in the control volumes' centers of gravity. The procedure discussed above is typical of the finite difference method. In numerical-analytical methods, the system of ordinary differential equations (1) can be directly integrated by means of one of the numerous methods used for solving ordinary differential equations [16, 31]. Runge- Kutta Method of 4th order ensures high solution accuracy. If the equation system (1) is linear, the matrix method can be applied; it requires the calculation of the exponential matrix e", where A is the coefficient matrix of the equation system (1). This method will be discussed in greater detail in Ex. 23.2.

Exercise 23.1 Integration of the Ordinary Differential Equation System by Means of the Runge-Kutta Method By applying the method of lines, which is used to discretisize only spatial derivatives in the transient heat conduction equation, one obtains the ordinary differential equation system

t = A(T)T + F(T,t) ,

(1)

where t is the vector of the first derivatives after time of the node temperatures, while the dimensions of the coefficient matrix A(T) are NEx NEo Coefficients of this matrix can be temperature dependent for a variable thermo-physical properties. Vector F(T), which in general depends on the

696


determined node temperatures, measures NE and is the boundary condition function. Discuss Runge-Kutta method of 4th order used for solving (1).

Solution Runge-Kutta method of 4th order is frequently used in practice, because it is highly accurate [6, 8, 16, 23, 51]. The accuracy order of the method is O[(~t)4].

Equation (1) will be written in the form

T=Q(T,t),

(2)

where Q(T,t) = A(T) T + F(T,t). Initial conditions have the form

Tlt=o

= To'

(3)

where vector To contains components, which are the temperatures in nodes at time t = O. Once the integration step ~t is assumed to be constant, temperatures T are calculated at time points t n = rust, n = 1, 2, ... according to the following algorithm: ~t

Tn+1 =Tn +-(k 1 +2k 2 +2k 3 +k 4 ) , 6

n=O, 1, ... ,

(4)

where

(5)

In the case of a single differential equation dT

-=Q(T,t), dt

algorithm (5) is simplified to a form

rl., = To

(6)

Exercise 23.1 Integration of the Ordinary Differential Equation System

697

n=O, 1, ... ,

(7)

where

(8)

In order to demonstrate the accuracy of the Runge-Kutta method of 4th order, [51] will be solved

dT= ( t+T-l -

)2

(9)

dt

with an initial condition (10)

T(O)=2.

The obtained solution will be compared with Euler method, according to which the (6) is solved as follows: (11)

n=O, 1, ...

The comparison results for I1t = 0,1 sand I1t = 0,05 s are presented in Table 23.1. The Table shows that the results obtained by means of the Runge-Kutta method are highly accurate. Table 23.1. The solutions of (1) obtained by means of the explicit Euler method and Runge-Kutta method of 4th order for the two integration steps: J1t J1t = 0.05 s -.mW-*W&:~$»~~~~~~w.'*UX*&~~~~x:&:~~~~

~'$::::m~~:=>1&S:-~::&~·; _. . . ·*Z.>::~l&&8r'?';;~~~~~~. - -.~£y~~~:.-

~~,~_~~r(~l~,=~~~_,,»_=_~!f (x)~.~,L",_»_~fJx) ~=~>_ ~ __~~_~ii~l~",«

Solving Direct and Inverse Heat Conduction Problems

Solving direct and inverse heat conduction problems

Solving Direct and Inverse Heat Conduction Problems